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Aeronautical vehicle

Subclass of:

701 - Data processing: vehicles, navigation, and relative location

701001000 - VEHICLE CONTROL, GUIDANCE, OPERATION, OR INDICATION

Patent class list (only not empty are listed)

Deeper subclasses:

Class / Patent application numberDescriptionNumber of patent applications / Date published
701004000 Altitude or attitude control or indication 235
701016000 With indication or control of landing 110
701014000 Flight condition indicating system 110
701015000 With indication or control of take-off 35
Entries
DocumentTitleDate
20130030610Automatic Estimation Process And Device For A Flight Parameter Vector In An Aircraft, As Well As Detection Methods And Assemblies For A Failure Affecting Such A Vector - Automatic estimation process and device for a flight parameter vector in an aircraft, as well as detection methods and assemblies for a failure affecting such a vector.01-31-2013
20100161157DEVICE FOR MANAGING PILOTING TASKS CARRIED OUT BY A CREW OF AN AIRCRAFT - The present invention lies in the field of embedded flight management systems on board aircraft. The invention relates notably to a system for managing alerts and procedures, and more precisely to a device for managing piloting tasks carried out by a crew of an aircraft. The device for managing tasks (06-24-2010
20100161153METHOD AND APPARATUS FOR AUTOMATICALLY DETERMINING STOPOVER AIRPORTS FOR FLIGHT PLANNING - A method and apparatus that automatically selects one or more stopover airports (or “technical stops”) for flight planning is disclosed. The method may include receiving flight origin, destination, aircraft identification information, aircrew identification information, passenger identification information, and user preference information from a user, receiving weather, safety-of flight and meteorological information based on at least the received origin and destination information, retrieving aircraft information, origin and destination airport information, potential stopover airport information, aircrew information, and passenger information from one or more databases based on at least one of the received flight origin, destination, aircraft identification information, aircrew information, passenger information, and user preference information, automatically selecting one or more stopover airports based on the received weather, safety-of flight and meteorological information and the retrieved flight origin, destination, aircraft information, aircrew information, passenger information, and user preference information, and outputting the selected one or more stopover airports to the user.06-24-2010
20100152925METHOD AND DEVICE FOR DETECTING OSCILLATORY FAILURES IN A POSITION SERVOCONTROL SUBSYSTEM OF AN AIRCRAFT CONTROL SURFACE - The detection device (06-17-2010
20110190965System and Method for an Integrated Backup Control System - Embodiments of the invention relate to a flight control system for controlling an aircraft in flight having a backup control system integrated into an active control stick. The actuated control stick may include a processing unit that includes independent and separate hardware and/or software dedicated to the primary control system and the backup control system. For the primary control system, the processing unit may receive a sensed primary control stick signal and communicate with a primary processor, which may be configured to generate a primary control signal. For the backup control system, the processing unit may receive a sensed backup control stick signal and generate a backup control signal. The processing unit may also generate tactile signal for use by the actuated control stick to adjust the feel of a pilot's control stick.08-04-2011
20130211633SENSOR FOR DETECTING HYDRAULIC LIQUIDS IN AIRCRAFT - The present invention relates generally to a system that monitors the condition of hydraulic systems for an aircraft or for other applications and, more particularly, to a system and method for detecting leakage within the hydraulic system aboard an aircraft. Such system is detecting hydraulic liquids by extended sensors based on the collapse of percolation conductivity (COPC) which sensors are covering an area in the aircraft.08-15-2013
20100145555Flight Control System - A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.06-10-2010
20100082184DISPLAYING AIR TRAFFIC SYMBOLOGY BASED ON RELATIVE IMPORTANCE - A method and system is provided for displaying aircraft symbology. The method includes displaying (04-01-2010
20110202206SYSTEM AND METHOD FOR INFORMING AN AIRCRAFT OPERATOR ABOUT A TEMPORARY FLIGHT RESTRICTION IN PERSPECTIVE VIEW - A system for informing aircraft operators about a temporary flight restriction (“TFR”) includes, but is not limited to, a display unit that is adapted for attachment to an aircraft. The display unit is configured to display graphical images. A processor is communicatively connected to the display unit and is configured to control the display unit. A receiver is communicatively connected to the processor and is configured to receive a broadcast containing information relating to the TFR (“TFR information”) and to automatically provide the TFR information to the processor. The processor is further configured to automatically control the display unit to display a three dimensional representation of an airspace that is subject to the TFR relative to the position of the aircraft when the processor receives the TFR information from the receiver.08-18-2011
20110202205SYSTEM AND METHOD FOR DISPLAYING CONTROL RELATED INFORMATION TO AN AIRCRAFT OPERATOR - A system for displaying throttle settings to an aircraft operator includes, but is not limited to, a display unit, a data storage unit configured to store aircraft and airport data, an operator input unit configured to receive thrust related information from the aircraft operator, an aircraft sensor configured to detect an aircraft condition, and a processor. The processor is communicatively connected to each of the above components and is configured to obtain therefrom the aircraft data, the airport data, the thrust related information, and the aircraft condition. The processor is also configured to calculate a first thrust requirement based on the aircraft data, the airport data, the thrust related information, and the aircraft condition, and to provide commands to the display unit to display either the first thrust requirement.08-18-2011
20110202204System and Method of Navigation based on State Estimation Using a Stepped Filter - Embodiments include systems and methods of navigation. In on embodiment, a plurality of position and motion states of a vehicle are estimated. The states may be estimated based on information received from a satellite receiver and an inertial measurement sensor. Estimating the states comprises performing one or more of a plurality of update steps at the rate that information is received from the satellite receiver. The states are estimated at a rate greater than the rate at which the update steps are performed. In one embodiment, the states are estimated using a stepped extended Kalman filter.08-18-2011
20100076623BRAKING PROCESS FOR AN AIRPLANE - An aircraft braking adaptation process is used to prevent rapid derotation of an aircraft causing damage to the front landing gear by formulating a braking command, applying the command to at least one brake, adapting the braking command by acquiring the aircraft trim and modifying the braking commands as a function of the aircraft trim.03-25-2010
20100114409METHOD OF INSPECTING THE INTEGRITY OF AN AVIONICS SYSTEM, AND AN INSPECTION DEVICE FOR IMPLEMENTING SAID METHOD - A method of inspecting the integrity of an avionics system (05-06-2010
20120245768DEVICE AND METHOD FOR EVALUATION OF THE OPERATIONAL CAPABILITIES OF AN AIRCRAFT - A device for evaluation of the operational capabilities of an aircraft for informing a user about the capabilities of the aircraft to carry out a mission. Included are means for detecting malfunctions of aircraft equipment adapted for functioning during a mission. An evaluation device includes means for acquisition of information about the mission; a means for calculating observed feasibility level of the mission on the basis of at least one detected malfunction and the information obtained about the mission of the aircraft; and a means for presenting a synthetic reactive indicator, representative of the observed feasibility level of the mission in at least one instant of the mission. The means for acquisition, calculation and presentation are adapted for functioning during the mission, to inform the user about the observed feasibility level of the mission depending on the detection of new malfunctions and/or the modifications of the mission in course.09-27-2012
20120245767SYSTEM AND METHOD FOR EVALUATING OPERATION OF A VEHICLE WITH RESPECT TO A PLURALITY OF ENVIRONMENTAL FACTORS - A system installed with a vehicle for evaluating operation of the vehicle with respect to environmental factors includes: (a) operational sensors for sensing data relating to operational factors of the environmental factors; (b) an operational information store coupled with selected sensors for storing operational data received from the selected sensors relating to the operational factors; (c) an operational standards store for storing operational standards associated with operating the vehicle; (d) an operational standard compliance evaluation unit coupled with the information store and coupled with the standards store for effecting comparison of the operational data with the operational standards to ascertain an operational comparison result, and determining whether the vehicle complies with the standards based upon the comparison result; and (e) an operational report and store unit coupled with the compliance evaluation unit for receiving the operational determination and generating at least one report relating to the operational determination.09-27-2012
20130079955SENSOR SYSTEM - Concepts and technologies are disclosed herein for a sensor system for detecting, characterizing, monitoring, and analyzing data. According to some embodiments disclosed herein, a monitoring system is configured to obtain data from a sensor system. The sensor system includes two or more sensors and can indicate an operating state detected at a monitored structure by the sensors. The monitoring system also obtains operational data including a threshold value for the sensors and an expected value for the sensors. The monitoring system is configured to adjust the thresholds based, at least partially, upon the operational data to obtain an adjusted threshold value, and to compare the data value to the adjusted threshold. The monitoring system can determine if the monitored structure is operating in an alarm condition.03-28-2013
20130079956METHOD OF REGULATING THE PROPULSIVE SPEED OF A HYBRID HELICOPTER - A method of regulating the propulsion speed of a hybrid helicopter. In application of a correction process for protecting the hybrid helicopter, piloting orders generated by a manual control member relate to an airspeed setpoint and they are corrected by control means in accordance with at least one correction mode in which the piloting orders are corrected in application of a rule that takes account of a setpoint consumed power corresponding to the airspeed setpoint derived from the piloting order.03-28-2013
20090150011METHOD AND DEVICE FOR GENERATING A SPEED PROFILE FOR AN AIRCRAFT DURING A TAXIING - A method and device for generating a speed profile for an aircraft rolling on the ground.06-11-2009
20100145552Route planning using ground threat prediction - Systems and methods are disclosed for determining an optimal flight path for an aircraft through a region of interest. A reroute region, which provides extreme boundaries for an optimal flight path, is defined around an initial flight path for the aircraft. A plurality of subregions are defined within the reroute region. Each of the plurality of subregions represent one of a plurality of representative times at which the airplane is expected to arrive at an associated location on the initial flight path. The position of at least one threat is predicted at each of the plurality of representative times. A cost is assigned to each cell in each subregion according to the predicted position of the at least one threat source at the representative time associated with the subregion. The optimal path is determined as a path through the reroute region having a lowest total cost.06-10-2010
20130035808AIRCRAFT WITH A CONTROL DEVICE - An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimising local lift coefficients on the aerofoil, depending on the flight state.02-07-2013
20130035807BIT TRANSMISSION VERIFICATION IN AN ARINC-BASED SYSTEM - An example data verification method includes communicating a bit from a transmitter module to a receiver module through a bus. The bit forms a portion of an ARINC word. The method verifies the bit at the bus using the transmitter module. An example data communication assembly includes a receiver module, and a data communication bus that communicates a bit to the receiver module. The bit forms a portion of an ARINC word. A transmitter module communicates the bit to the data communication bus. The transmitter module monitors communication of the bit from the data communication bus to the receiver module.02-07-2013
20100036547System and methods for on-board pre-flight aircraft dispatching - Systems and methods for providing pre-flight dispatching are disclosed. In one embodiment, a system for on-board dispatching of an aircraft includes a flight dispatching apparatus positioned within the aircraft that is configured to perform one or more flight dispatching tasks. A communications apparatus is configured to exchange wireless signals between the dispatching apparatus and one or more ground-based facilities. In another embodiment, a method of dispatching an aircraft includes designating a person to perform predetermined dispatching tasks, and establishing a wireless data connection between the aircraft and at least one ground-based facility. Information obtained from the at least one ground-based facility is then processed to perform the one or more dispatching tasks, and at least a portion of the processed information is communicated to the at least one ground-based facility using the wireless data connection.02-11-2010
20130138268MULTI CORE VEHICLE MANAGEMENT MULTI CORE MANAGER SYSTEM AND METHOD - A computerized method for transmitting data between a multi core vehicle management system and a vehicle system. The method can include receiving, at a vehicle management system computer, a vehicle system request message from a requesting vehicle management system component. The requesting vehicle management system component can be one of a plurality of vehicle management system components, and the vehicle system request message can have a destination vehicle system component. The method can include generating a sanitized vehicle system request message based on the requesting vehicle management system component and the destination vehicle system component. The sanitized vehicle system request message can be transmitted to said destination vehicle system component.05-30-2013
20120265372AVIONICS DATA ENTRY DEVICES - Methods, systems, and apparatuses for the use of a wireless portable avionics device in conjunction with on-board flight systems and/or off-board service providers. The device may be used by aircraft personnel such as pilots and may act as a command/data entry and/or display tool to augment cockpit display systems. The device can receive flight data (e.g., a flight plan) from an off-board provider and automatically transfer it, as well as any previously prepared commands or data, to a flight management system and/or cockpit display systems. Commands and/or data (including pre-existing ones and ones entered in real-time) can be wirelessly transferred to the on-board flight systems which are not in direct physical contact with the device. Thus, the device can be easily manipulated during turbulence or under poor readability conditions. The device can be used to manipulate items shown on cockpit display systems in a timely and accurate manner.10-18-2012
20130211630FORCE GENERATOR FOR MOUNTING ON A STRUCTURE - The invention relates to a force generator (08-15-2013
20130041528Intelligent modular aerospace system - An Intelligent Modular Aerospace System (IMAS) is a paradigm shift in the architecture, utility, efficiency, operation, test/checkout, qualification testing and adaptability of an aerospace application system that provides Time/Space/Position Information, Data Acquisition/Processing/Relay, Power Generation/Distribution, avionic solutions, navigation, and command/data handling. IMAS (02-14-2013
20130041527VARIABLE BANDWIDTH CONTROL ACTUATION METHODS AND APPARATUS - Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.02-14-2013
20100114407METHODS AND SYSTEM FOR TIME OF ARRIVAL CONTROL USING AVAILABLE SPEED AUTHORITY - Methods and a system for a vehicle control system using a reference time profile including an upper control bound and a lower control bound are provided. The system includes an input device configured to receive a required time of arrival at a waypoint and a processor communicatively coupled to said input device wherein the processor is programmed to generate a reference time profile using a first speed profile up to an intermediate control point and a second speed profile between the intermediate control point and an RTA waypoint. The system also includes an output device communicatively coupled to the processor wherein the output device is configured to transmit a speed control signal based on the reference time profile to a vehicle speed control system.05-06-2010
20100100259FAULT DIAGNOSIS DEVICE AND METHOD FOR OPTIMIZING MAINTENANCE MEASURES IN TECHNICAL SYSTEMS - The present invention provides a fault diagnosis device for optimizing maintenance measures in a system, in particular a flying object. The diagnosis device has a storage unit for storing diagnosis rules, which each have a fault condition indicating the presence of a fault, and a fault conclusion formed by logical combinations of potential fault causes of the respective fault. Furthermore, a logic unit is provided, which logically combines those stored fault conclusions whose associated fault conditions are met and, on the basis of the combined fault conclusions, determines a logical diagnosis result having at least one fault cause hypothesis. A calculation unit subsequently calculates an occurrence probability for each fault cause hypothesis of the logical diagnosis result determined.04-22-2010
20100100258Method of Ergonomically Selecting a Reference Course/Radial for the Guidance of an Aircraft - The invention relates to a method and an associated device making it possible to avoid guidance command input errors by the crew. Since the course and the radial are linked by different relationships depending on whether the aircraft is approaching or moving away from a point, the procedures from air traffic control may be given either in course or in radial, and since the FMS system can also require the input of one of the two values, the number of possible different combination creates a situation of ambiguity that is prejudicial to the safety of the flight. To resolve this problem, the invention proposes a systematic display in text mode and/or in graphic mode of the input datum (course or radial) and of the other for verification by the crew.04-22-2010
20100042268APPARATUS, AND ASSOCIATED METHOD, FOR TRACKING AIRCRAFT STATUS - An apparatus, and an associated method, provides a visualization of an aircraft status relative to a scheduled airline timeline for the aircraft. Input information associated with the aircraft and operations associated therewith, are provided and detected. The input information is used to generate a timeline having one or more milestones and an aircraft icon. The timeline and the aircraft icon are together displayed by a displayer. The visualization is viewable by airline personnel, permitting their viewing of the visualization.02-18-2010
20100042267PROGRAMMABLE REVERSE THRUST DETENT SYSTEM AND METHOD - A reverse thrust detent system for an aircraft includes a throttle quadrant having an intermediate reverse thrust detent position, a reverse thrust scheduling system interfacing with the throttle quadrant, at least one aircraft engine interfacing with the reverse thrust scheduling system and a programmable input interfacing with the reverse thrust scheduling system and adapted to receive an engine reverse thrust setting. The reverse thrust scheduling system is adapted to operate the at least one aircraft engine according to the engine reverse thrust setting responsive to actuation of the intermediate reverse thrust detent position of the throttle quadrant. A reverse thrust detent method for an aircraft is also disclosed.02-18-2010
20100049377SENSOR AND ANTENNA ARRANGEMENT - An exemplary sensor for an aircraft includes a sensor mountable within an aircraft and operative to communicate wirelessly communications to a distributed aperture antenna. The sensor is operative to harvest energy from the aircraft to power the sensor.02-25-2010
20090157236Intelligent system and method for spacecraft autonomous operations - The intelligent system for autonomous spacecraft operations includes an on-board Autonomous Operations subsystem integrated with an on-ground Web-based Remote Intelligent Monitor System (RIMS) providing interface between on-ground users and the autonomous operations intelligent system. The on-board Autonomous Operation subsystem includes an On-Orbit Checkout Engine (OOCE) unit and an Autonomous Tasking Engine (ATE) unit. Spacecraft Command Language (SCL) engine underlies the operations of the OOCE, ATE and RIMS, and serves as an executer of commands sequences. The OOCE uses the SCL engine to execute a series of SCL command scripts to perform a rapid on-orbit checkout of subsystems/components of the spacecraft in 1-3 days. The ATE is a planning and scheduling tool which receives requests for “activities” and uses the SCL scripts to verify the validity of the “activity” prior to execution, and scheduling the “activity” for execution or re-scheduling the same depending on verification results. Automated Mission Planning System (AMPS) supports the ATE operations. The ATE uses a priority schedule if multiple “activities” are to be executed.06-18-2009
20090157235METHOD AND APPARATUS FOR MOVING A SWING TAIL CARGO DOOR ON AN AIRCRAFT - A computer implemented method, apparatus, and computer usable program code for a mobile tail support control system. An apparatus comprises a data processing system, an output device, a set of load sensors, a set of position sensors, and a computer program product executing on the data processing system. The output device is capable of generating signals for managing movement of a mobile tail support apparatus. The set of load sensors may be coupled to the data processing system and may be capable of detecting loads associated with a swing tail cargo door. The set of position sensors are coupled to the data processing system and detect a position of the mobile tail support apparatus relative to the swing tail cargo door. The computer program product may receive information from the set of load sensors and the set of position sensors and generate signals to manage the mobile tail support apparatus.06-18-2009
20090157234Regenerative integrated actuation system and associated method - A regenerative integrated actuation system and method are provided to efficiently supply power to a plurality of actuators and to make efficient use of power regenerated by the actuators. The system may include a plurality of actuators in communication with a power distribution system. Each actuator may include an energy storage element. The system may also include a controller for determining if a respective actuator is in a consumption mode or a regenerative mode. If in the consumption mode, the controller may determine whether the respective actuator should draw power from an energy storage element or from the power distribution system. Conversely, if in the regenerative mode, the controller may determine whether any excess power from the respective actuator should be provided to one of the actuators, such as to another actuator which is in the consumption mode or to the energy storage element associated with the respective actuator.06-18-2009
20090157233SYSTEM AND METHODS FOR AUTONOMOUS TRACKING AND SURVEILLANCE - A system and methods for autonomously tracking and simultaneously providing surveillance of a target from air vehicles. In one embodiment the system receives inputs from outside sources, creates tracks, identifies the targets and generates flight plans for unmanned air vehicles (UAVs) and camera controls for surveillance of the targets. The system uses predictive algorithms and aircraft control laws. The system comprises a plurality of modules configured to accomplish these tasks. One embodiment comprises an automatic target recognition (ATR) module configured to receive video information, process the video information, and produce ATR information including target information. The embodiment further comprises a multi-sensor integrator (MSI) module configured to receive the ATR information, an air vehicle state input and a target state input, process the inputs and produce track information for the target. The embodiment further comprises a target module configured to receive the track information, process the track information, and produce predicted future state target information. The embodiment further comprises an ownship module configured to receive the track information, process the track information, and produce predicted future state air vehicle information. The embodiment further comprises a planner module configured to receive the predicted future state target information and the predicted future state air vehicle information and generate travel path information including flight and camera steering commands for the air vehicle.06-18-2009
20100106346METHOD AND SYSTEM FOR MANAGING FLIGHT PLAN DATA - Method and systems for managing flight plan data associated with an aircraft are provided. A list of navigational entry selections (e.g., flight plan origins and flight plan destinations) is generated. Each of the navigational entry selections is associated with the aircraft (e.g., previously used). The list of navigational entry selections is displayed to a user of the aircraft. An indication of a selection of at least one of the navigational entry selections is received from the user. The navigational entry selections are generated, for example, based on navigational entries previously stored in a memory on-board the aircraft, a location of the aircraft, or a combination of the previous navigational entries and the location of the aircraft.04-29-2010
20100106347INDEPENDENT BRAKE CONTROL OF A COMMON AIRCRAFT GEAR - A brake control system for a landing gear of an aircraft is provided. The system includes a first control channel for providing brake control signals to one or more brakes on the landing gear, and a second control channel for providing brake control signals to another one or more brakes on the landing gear. At least one of the first control channel and the second control channel is configured to act as an executive in monitoring braking efforts applied by the one or more brakes as compared to braking efforts applied by the another one or more brake, and to cause the braking efforts of at least one of the one or more brakes or the another one or more brakes to be modified in an effort to equalize the braking efforts.04-29-2010
20120185116INTEGRATED BLEED AND ENGINE CONTROLLER - An integrated electronic engine control and environmental control system bleed control apparatus for use with an aircraft engine. The apparatus comprises an electronic engine controller, an environmental control system bleed controller for controlling a flow of bleed air from the aircraft engine to an environmental control system located in an aircraft fuselage, and a housing for mounting on or near the aircraft engine. The housing contains both the electronic engine controller and the environmental control system bleed controller.07-19-2012
20100042269SYSTEM AND METHODS RELATING TO AUTONOMOUS TRACKING AND SURVEILLANCE - A method of protecting an asset using at least one unmanned vehicle. The method includes establishing a plurality of boundaries around the asset. The boundaries define edges of zones. The method further includes observing a target in a first one of the zones. The method further includes deploying the unmanned vehicle to a location in a vicinity of the asset and tasking the vehicle to perform a first defensive measure as long as the target remains in the first zone. If the target crosses a boundary from the first zone into a second one of the zones, where the second zone is more proximate to the asset than the first zone, the method further includes tasking the vehicle to perform a second defensive measure.02-18-2010
20090125165METHOD AND DEVICE FOR PILOTING A PITCHING AIRCRAFT - The invention relates to a method and device for piloting a pitching aircraft. The inventive device (05-14-2009
20090125164Integrated electronic module for visualizing digital instruments on a display - An electronic control unit includes in combination: a data collection element form sensors and instruments existing on board of the transport device, a collected-data processing element, a data storage element, a graphic display element, a radio communication element, and an input/output pilot interface element. The storage element includes a removable or fixed memory card.05-14-2009
20130046422ONBOARD FLIGHT PLANNING SYSTEM - According to the application, a method for generating a flight route of an aircraft by an aircraft based computer system is disclosed. The method comprises the execution the following steps, which are executed by the aircraft based computer system. A mission specific data subset is received from a ground system. It is checked whether there are predefined routes from a departure airport to a destination airport. If it is determined that predefined route are available which are in accordance with over-flight permissions the predefined routes are used as a set of candidate routes for deriving a flight route. Otherwise, a set of proposed flight routes is generated which comprises at least one proposed flight route. Over-flight permissions are checked for the set of proposed flight routes. The steps of generating a set of proposed flight routes and of checking the over-flight permissions are repeated until at least one proposed flight route is found to be in accordance with the over-flight permissions. The one or more flight routes or routes which are in accordance with the over-flight permissions are used as a set of candidate routes for deriving a flight route. A flight route is derived from the set of candidate routes.02-21-2013
20110010026Calibration Method for Aerial Vehicles - Aerial vehicles make good remote sensing platforms by reducing the cost and making imagery easier to obtain. The low altitude, small image footprint and high number of images make it difficult and tedious to georeference the images based on features. Auto-orthorectification techniques based on the position and attitude of the aerial vehicle would work well except the inherent errors in the aerial vehicle sensors reduce the accuracy of the orthorectification significantly. The orthorectification accuracy is improved by calibrating the aerial vehicle sensors. This is done by inverse orthorectifing the images to find the actual position and attitude of the aerial vehicle using ground references setup in a square.01-13-2011
20100268403VEHICLE MONITORING SYSTEM - An example reconfigurable vehicle monitoring arrangement includes a housing securable relative to a vehicle, a communication base at least partially disposed within the housing, and a universal connector assembly configured to selectively operatively connect the communication base with a plurality of different modules. At least one of the modules is configured to communicate data gathered from a plurality of vehicle data sources to the communication base.10-21-2010
20090306838METHOD AND DEVICE FOR AIDING THE MAINTENANCE OF A SYSTEM - The invention relates to a method for aiding the maintenance of a system, the system comprising a set of networked elements, the system being accompanied by indications defining subsets of networked elements E12-10-2009
20090306836Aircraft Emergency Handling - The present invention provides methods and apparatuses that reduce pilot workload and increase the performance and efficiency of the pilot's control of the aircraft. The present invention comprises methods and apparatuses for determining the presence and type of an emergency condition, for example by detecting corresponding sensor outputs or by accepting input from a pilot or a combination thereof; and then responding to that emergency by initiating a pre-determined set of actions specific to the determined emergency. Embodiments of the invention can include the ability to monitor engine conditions as well as control electrical functions such as the fuel boost pump, alternator field, battery contactor and other important electrical devices. Some examples described below assume a single-engine piston aircraft for ease of illustration. The invention can also be applied to multi engine and turbine powered aircraft as well.12-10-2009
20090306837Aircraft Exhaust Gas Temperature Monitor - A computer-implemented function monitors and displays exhaust gas temperatures (EGT) in a plurality of cylinders in an engine. The invention provides an easy way to read exhaust gas temperature on a specific cylinder, and to provide a means for leaning the engine while in a climb. Efficient leaning in a climb reduces fuel consumption and reduces the chance of harmful conditions that can lead to engine failure.12-10-2009
20130073123Energy Control Apparatus For Controlling Hybrid Energy Sources For An Aircraft - An energy control apparatus for controlling hybrid energy sources for an aircraft is designed for determining an operating characteristic of an energy source, a demand of at least one first consumer for a first resource and a demand of a second consumer for a second resource. The energy control apparatus activates the energy source in dependence on the demand for the first resource and the second resource and, if there is no demand for a first or second resource that is generatable by the energy source and is present in excess, supplies a third consumer with the excess resource. This makes it possible for an energy system to operate different consumers independently of the type of generated resources and their dependencies during the generation.03-21-2013
20130060404SYSTEMS AND METHODS FOR BRAKING SYSTEM TESTING - Systems and methods disclosed herein may be useful for testing braking systems for use in, for example, an aircraft. A system is disclosed that allows for built in testing. For example, a method if provided comprising sending, from a brake controller, a test command set to at least one of an electromechanical actuator (EMAC) and a brake servo valve (BSV) in response to a landing gear retraction, receiving, at the brake controller, feedback from the at least one of the EMAC and the BSV in response to the test command set, and comparing, at the brake controller, the feedback with a predetermined signature.03-07-2013
20130060405FLIGHT CONTROL SUPPORT DEVICE - Disclosed is a flight control support device which sets a flight restricted area W along a terrain, thereby achieving improvement in safety of a small aircraft A and sufficiently securing the degree of freedom of flight course selection of a pilot. The flight control support device includes a terrain information acquirer, an aircraft information acquirer, a flight restricted area setter which sets the flight restricted area W along the terrain on the basis of the terrain information acquired by the terrain information acquirer and the aircraft information acquired by the aircraft information acquirer, and a flight control supporter which supports flight control of a flying object on the basis of the flight restricted area set by the flight restricted area setter.03-07-2013
20120310451METHOD AND DEVICE FOR MEASURING THE ANGULAR VELOCITY OF A LUMINANCE TRANSITION ZONE AND STEERING AID SYSTEM FOR FIXATION AND TRACKING A TARGET COMPRISING AT LEAST ONE SUCH LUMINANCE TRANSITION ZONE - The present invention relates to a method for measuring a time delay between two output signals measured by two adjacent optical sensors, the time delay resulting from a movement of an object moving in a given direction. The method comprises the steps: 12-06-2012
20090299552METHOD AND SYSTEM FOR AUTOMATICALLY MANAGING A CONVOY OF AIRCRAFT DURING A TAXIING - The system (12-03-2009
20090299551SYSTEM AND METHOD FOR MULTIPLE AIRCRAFT LIFTING A COMMON PAYLOAD - A system and method are provided for controlling a plurality of aircraft to lift a common payload. The system comprises of multiple aircraft tethered to a common payload, where the group of said aircraft form a swarm that is controlled by a pilot station. Each said aircraft is autonomously stabilized and guided through a swarm avionics unit, which further comprises of sensor, communication, and processing hardware. At the said pilot station, a pilot remotely enters payload destinations, which is processed and communicated to each said aircraft. The method for controlling a multi-aircraft lifting system comprises of first inputting the desired location of the payload, and then determining a series of intermediary payload waypoints. Next, these payload waypoints are used by the swarm waypoint controller to generate individual waypoints for each aircraft; a flight controller for each aircraft moves the aircraft to these individual waypoints.12-03-2009
20090292406METHODS AND SYSTEMS FOR REDUCING THE PHENOMENON OF STRUCTURAL COUPLING IN THE CONTROL SYSTEM OF AN IN-FLIGHT REFUELLING BOOM - A method for controlling a boom (11-26-2009
20090030564METHOD AND APPARATUS FOR MANAGING INSTRUMENT MISSED APPROACHES - A computer implemented method, apparatus, and computer usable program code for managing missed approaches to runways. In one advantageous embodiment, an event requiring missing an approach to a runway by an aircraft is monitored for, while the movement of the aircraft along a route is being controlled by a flight management system. Responsive to detecting the event, a location of the aircraft is identified to form an identified location. The identified location of the aircraft is compared to a plurality of waypoints for a plurality of missed approach routes to identify an active waypoint in the plurality of waypoints closest to the aircraft to form an identified waypoint. A missed approach route from the plurality of missed approach routes associated with the identified waypoint is executed for the aircraft.01-29-2009
20120116615Secure Terminal Data Loader Apparatus and Method for a Mobile Platform - A terminal data loading device on a mobile platform includes a media unit for receiving a transportable media element containing media data and outputting a media signal to a control processor unit. The control processor unit outputs an information signal to a wireline communication unit. The wireline communication unit outputs a wireline signal to a network on the mobile platform.05-10-2012
20120116612IMPLEMENTATION OF KALMAN FILTER LINEAR STATE ESTIMATOR FOR ACTUATOR EQUALIZATION - A rotorcraft control system is provided and includes a rotor blade having a moving surface operatively connected for movement among various positions, an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions, a sensor operably coupled to the actuator to generate a sensor response signal reflective of a response of the actuator to the modified control signal and a controller to output the modified control signal to the actuator, the controller including a control loop to generate the modified control signal from an initial control signal that is modified by relating the initial control signal and the sensor response signal and by accounting for actuator inaccuracies, sensor sensitivities and noise.05-10-2012
20120116611Managing Control Surfaces for an Aircraft - A method and apparatus for managing a number of control surfaces for an aircraft. A current configuration for the number of control surfaces for the aircraft is identified during flight of the aircraft. A selected point in time at which the current configuration for the number of control surfaces is to be changed to a new configuration for the number of control surfaces is identified. A portion of time relative to the selected point in time during which the current configuration for the number of control surfaces is to be changed to the new configuration is identified based on a difference between a current amount of energy for the aircraft and an expected amount of energy for the aircraft.05-10-2012
20120116610AUTOMATIC CONTROL OF AN AIRCRAFT IN THE EVENT OF FLIGHT CREW INCAPACITY - A method for automatic control of an aircraft in event of flight crew incapacity may include determining any incapacity of the flight crew. The method may also include providing a message requiring acknowledgement from the flight crew in response determining incapacity of the flight crew. The method may additionally include commanding an auto pilot to control the aircraft in response to not receiving acknowledgement from the flight crew.05-10-2012
20130166110AIRCRAFT WITH AN ARRANGEMENT OF FLOW-INFLUENCING DEVICES - An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.06-27-2013
20130166111METHOD FOR CONTROLLING A HIGH-LIFT DEVICE OR A FLIGHT CONTROL SURFACE, SYSTEM AND AIRCRAFT OR SPACECRAFT - The present invention discloses a method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an aircraft or spacecraft.06-27-2013
20130166112Method and Device for Determining a Lateral Trajectory of an Aircraft and Associated Flight Management System - A method, and an associated device, is provided for the determination, by a flight management system of an aircraft, of a lateral trajectory of said aircraft on the basis of a predefined flight plan allowing consecutive conflicts to be resolved in an improved manner. This allows an improved lateral trajectory to be designed in the case where multiple trajectory conflicts exist. The trajectory obtained is closer to the flight plan defined by the pilot. The propagation of trajectory conflicts to the following flight segments is thus avoided. In fact, instead of propagating the trajectory conflict from one resolution to another, the method allows the conflict to be resolved in a space delimited at most by the input of the first conflict and the output of the last conflict.06-27-2013
20090012660Air Traffic Control - An air traffic control system, for use by a controller controlling multiple aircraft, comprising a processor, an input device and a display device, further comprising: trajectory prediction means for calculating a trajectory for each aircraft, for inputting aircraft detected position data, and for recalculating the trajectories based on said position data, and conflict detection means for detecting, based on the trajectories, future circumstances under which pairs of aircraft violate predetermined proximity tests, and for causing a display on the display device indicating said circumstances, further comprising means for inputting instruction data corresponding to instructions issued by the controller to an aircraft, and in which the proximity indication means is arranged to use a first proximity test and a second, more restrictive, proximity test; and in which the system is arranged to display a symbol representing pairs of aircraft which violate the second test in a first display mode, and those which violate the first set but not the second set in a second display mode, and in which the system is arranged, on input of a said instruction by a controller in relation to a pair of aircraft, to change the display mode of the symbol for said pair from the second mode to a third mode indicating that no further action is necessary.01-08-2009
20090012659Manual Human Interfaces to Electronics - In accordance with one embodiment of the present disclosure, a method for controlling an aircraft by a hands on throttle-and-stick (HOTAS) includes selectively connecting, by the HOTAS, two interfaces of a controller for the aircraft. The selective connection is made through one of a plurality of possible paths. Each path has an expected respective voltage drop within a predetermined range. The selected one of the possible paths connecting the two interfaces is determined by determining an actual voltage drop associated with the selected path. A control operation for the aircraft is effected by the controller based on the determined selected path. The method reduces the number of required electrical connections.01-08-2009
20090012658CONTROL SURFACE FAILURE DETECTION FOR FLY-BY-WIRE AIRCRAFT - A flight control system which detects a failure of a flight control surface and performs at least one action in response to the detected failure.01-08-2009
20090012657AUTONOMOUS OUTER LOOP CONTROL OF MAN-RATED FLY-BY-WIRE AIRCRAFT - The present invention is directed to a control system for use on a fly-by-wire (FBW) aircraft. The system includes a controller coupled to the FBW aircraft. The controller is configured to generate a plurality of simulated pilot control signals from at least one aircraft maneuver command. The plurality of simulated pilot control signals are generated in accordance with a predetermined control law. The at least one aircraft maneuver command is derived from at least one command telemetry signal received from a remote control system not disposed on the FBW aircraft. The plurality of simulated pilot control signals are configured to direct the FBW aircraft to perform an aircraft maneuver in accordance with the at least one aircraft maneuver command.01-08-2009
20120271490METHOD FOR DISTRIBUTING BRAKING TORQUE BETWEEN BRAKED WHEELS FITTED TO AT LEAST ONE UNDERCARRIAGE OF AN AIRCRAFT - A method for distributing braking energy between a group of braked wheels 1 . . . p and fitted to N undercarriages of an aircraft, each of the braked wheels comprising a brake furnished with a stack of discs to which a load is selectively applied so as to generate a torque for braking the wheel. Each brake is equipped with means for measuring a thickness of the stack of discs, and in which: 10-25-2012
20090177339Optimization and Mechanization of Periodic Flight - The implementation of periodic flight for enhancing aircraft's endurance or range is described having at least two components in the periodic flight embodiments. The first component is the trajectory optimization which determines the optimal periodic trajectory (such as altitude, velocity and flight path angle) that produces maximal endurance or range for a given fuel. The second component is the periodic guidance law which mechanizes the optimal periodic trajectory. For certain aircraft, periodic flight improves that aircraft's endurance or range over steady state flight.07-09-2009
20110282521Aviation Application Setting Antenna Array and Integrated Temperature Sensor - An antenna array for use in an aviation application setting comprises an external covering and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. A deposit of phosphor material is also disposed beneath this covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering can be fixed to an exterior surface of an aircraft. The four radio frequency antennas are electrically discrete from one another though also being configured as an integral mechanical structure. The phosphor material, in turn, can serve to facilitate detection of a parameter of interest, such as temperature or airspeed.11-17-2011
20090319098SYSTEM FOR DISPLAYING REQUIRED NAVIGATION PERFORMANCE ON A HORIZONTAL SITUATION INDICATOR - A display system is provided that renders a horizontal situation indicator that includes required navigation performance (RNP) and estimated position uncertainty (EPU) values rendered non-numerically and in a fairly intuitive manner. A processor receives at least data representative of a desired course of the aircraft, data representative of the RNP for the aircraft, and data representative of the EPU for the aircraft. The processor renders, on a display device, a horizontal situation indicator that includes an aircraft symbol representative of a top-down view of the aircraft, an RNP boundary graphic representative of at least one RNP boundary for the aircraft, and an EPU graphic representative of the EPU for the aircraft. The aircraft symbol is rendered at a position that is representative of actual aircraft position relative to the desired course, and the RNP boundary graphic is rendered at a position relative to the rendered aircraft symbol and comprises a shaded region that shades a portion of the display device.12-24-2009
20100152924NEXT GENERATION ELECTRONIC FLIGHT BAG - An electronic flight bag for an aircraft includes a display device and a processing system. The display device is operable to render various images. The processing system is in operable communication with the display. The processing system is configured to receive various types of data from various aircraft systems and is operable, upon receipt of the data, to supply display commands to the display device that cause the display device to automatically render various images. These images may include, among other things, flight manual pages, checklists, approach charts, maintenance data, and various navigation displays. The electronic flight bag may also implement the functions of various other aircraft systems and devices.06-17-2010
20090177338FAILSAFE REMOTE DATA CONCENTRATOR - A remote data concentrator receives signals from a plurality of sensors. Each of the sensors have their signals split between at least two flow paths, such that each of the sensors are provided with redundancy.07-09-2009
20110040429ACTIVE VIBRATION DAMPING (AVD) SYSTEM FOR PRECISION POINTING SPACECRAFT - An active vibration damping (AVD) control system for spacecraft provides a simple-to-implement and robust formulation that provides a novel damping control method for reducing spacecraft structural vibrations and improving antenna and instrument pointing. The AVD control system comprises an excitation signal generator configured to generate excitation input signals, and a damping model identification unit configured to receive system identification data and configured to produce control model parameters, the system identification data comprising the excitation input signals and information associated with motion of the spacecraft. The AVD control system further comprises an AVD control unit configured to receive the control model parameters, the AVD control unit configured to produce AVD control signals to control one or more actuators of the spacecraft.02-17-2011
20100305780FLIGHT CONTROL SYSTEM AND METHOD OF SEPARATING CONTROL LEVER LINKAGE - A flight control system according to the present invention includes a first sensor, a flight control computer, a link mechanism, a separation unit, and a second sensor detecting a force transmitted from the first control lever to the link mechanism. The first sensor detects a force applied from an outside to a first control lever. The flight control computer determines whether or not stacking arises in the first control lever on the basis of the force detected by the first sensor and the force detected by the second sensor, and outputs a separation command to the separation unit when determining that the stacking arises. The separation unit disconnects the link mechanism on the basis of the separation command to separate a connection between the first control lever and the second control lever.12-02-2010
20100010692Integrating avionics system with single event upset autonomous recovery - A novel system and method for detecting and recovering from single event upsets in integrating processing systems are presented. Two delta value processing lanes may be utilized to process raw data from inertial sensors. The output of the two processing lanes may be compared to detect the presence of an SEU. If an error is detected, a previously stored set of delta values may be utilized by the system. Additionally, the system may contain a temporary buffer to store calculated delta values in the event of a processor reset caused by an SEU or other error. The temporary buffer may store delta values accumulated during the processor reset and may furnish these stored delta values to the processor once it has finished resetting. The stored delta values may then be batch-processed and applied to system state values saved to memory prior to the processor reset.01-14-2010
20120191273 AIRCRAFT FLIGHT DATA DELIVERY AND MANAGEMENT SYSTEM WITH EMERGENCY MODE - An automated aircraft flight data and delivery management system and method operates in a normal state and a demand state. The demand state may be self-initiated or manually-initiated, and may be triggered during situations which include but are not limited to situations when the aircraft is in a potential or confirmed emergency situation. Data transmission increases in intensity when the system is in a demand state.07-26-2012
20110295448SYSTEM ABOARD AN AIRCRAFT - The invention relates to a device aboard an aircraft comprising output means (12-01-2011
20090055034INERTIAL NAVIGATION UNIT PROTOCOL CONVERTER - A protocol converter that translates the ARINC-429 protocol output of an Inertial Navigation System to the National Marine Electronics Association 02-26-2009
20100324757Method and Device for Optimizing the Deceleration Point of a Holding Circuit - A method for optimizing the computation of the position of the braking point on the approach to a holding circuit for aircraft is provided. The method comprises computing the optimal position of the theoretical deceleration point allowing the aircraft to pass from its current speed to the maximum speed authorized at the entry point and of the theoretical deceleration distance, computing a trajectory portion forming a turn allowing the aircraft to enter the holding circuit and the position of the point of the start of the turn, computing a point for anticipating the turn, making it possible to take into account the banking rate of the aircraft, computing a margin, and computing the start-of-braking point, situated at a distance.12-23-2010
20090030565METHODS OF DETECTING MISALIGNMENT OF POINTS BELONGING TO AN AIRCRAFT FLIGHT PLAN - A method of detecting the misalignment of a first point (01-29-2009
20110144833SYSTEMS AND METHODS FOR PROVIDING AN IN-TRAIL PROCEDURE SPEED DIRECTOR - Embodiments of the present invention enhance existing ITP algorithms by providing additional information to the flight crew. The additional information may enable the flight crew to appropriately modify own aircraft airspeed, and thereby, ground speed, in order to qualify for ITP procedures.06-16-2011
20090248225Apparatus For An Automated Aerial Refueling Boom Using Multiple Types Of Sensors - A system for automated control of a refueling boom coupled to a tanker aircraft is provided. The system includes: a first inertial measurement unit (IMU) providing inertial measurements for the tanker aircraft; a first GPS receiver providing a GPS location for a GPS antenna attached to the tanker aircraft; and a processor adapted to calculate a first inertial navigation state for the tanker aircraft through integration of the inertial measurements, the processor being further adapted to calculate a first inertial navigation state error relative to the GPS location and to filter the first inertial navigation state error and the first inertial navigation state based upon noise characteristics of the first IMU and the first GPS receiver to provide an updated inertial navigation state for the tanker aircraft, the processor being further adapted to control the refueling boom relative to a receiver aircraft based upon the first and updated inertial navigation states.10-01-2009
20100114410METHOD OF ENSURING THE INTEGRITY OF FLIGHT DATA AND A SYSTEM FOR IMPLEMENTING SAID METHOD - A method of transferring and processing flight data of an aircraft including recording the aircraft flight data in an onboard avionics system in a digital format so as to obtain digital data, the flight data including safety impact flight data and flight data having no recognized effect on safety. The method further includes recording at least the safety impact flight data in the onboard avionics system in an additional format dissimilar to the digital format so as to obtain additional flight data, storing the digital data and the additional flight data separately, transferring the digital data and the additional flight data to a monitoring computer on the ground, displaying the digital data on a screen in the form of display digital data, and transferring the digital data and the additional flight data to a complementary interpretation unit so as to generate one of display data and print data relating to the additional flight data.05-06-2010
20100049380METHOD AND SUPPORT DEVICE FOR AIDING IN THE PREPARATION AND MANAGEMENT OF MISSIONS IN AIRCRAFT - The invention in particular has as its object a method and a device for an operating center for aiding in the preparation and management of missions of an aircraft. After a plurality of digital data has been received (02-25-2010
20100114406METHOD AND SYSTEMS FOR REQUIRED TIME OF ARRIVAL PERFORMANCE DISPLAY - A method and system for a required time of arrival (RTA) performance graphic display is provided. The system includes a processor programmed to receive a required time of arrival and a first visual display communicatively coupled to the processor. The first visual display includes an RTA graphic having a dial substantially symmetric about an axis, a first marker indicative of a current estimated time of arrival (ETA) at a predetermined waypoint, a second marker indicative of a value of the RTA relative to the current ETA value and a selected RTA time tolerance value, a first indication representing a first time the vehicle can attain the predetermined waypoint, a second indication representing a last time the vehicle can attain the predetermined waypoint, a third indication representing the uncertainty of the ETA in an early arrival direction, and a fourth indication representing the uncertainty of the ETA in a late arrival direction.05-06-2010
20090312892DISTRIBUTED ENGINE CONTROL SYSTEM - A distributed engine control system is provided. The engine control system includes first and second engine data concentrators. Each of the first and second engine data concentrators include a processor module, a signal conditioning module coupled to the processor module, a data transfer module coupled to the processor module, and a data bus coupled between the first and second engine data concentrators and a hydro-mechanical unit (HMU).12-17-2009
20090150010METHOD AND DEVICE FOR GENERATING A YAW SPEED ORDER FOR AN AIRCRAFT DURING A TAXIING - The device (06-11-2009
20090150009METHOD AND DEVICE CONCERNING THE TAXIING OF AN AIRCRAFT, WHICH IS AUTOMATIC AT LEAST IN PART - Method and device for the at least partially automatic driving of an aircraft rolling on the ground.06-11-2009
20090150008METHOD AND DEVICE FOR GENERATING A SPEED FOR AN AIRCRAFT DURING A TAXIING - Method and device for generating a controlled speed for an aircraft rolling on the ground.06-11-2009
20090005916Systems and methods for communication, navigation, surveillance and sensor system integration in a vehicle - A system and method are provided for facilitating substantially seamless interface between individual component systems for sensor fusion, data exchange, and communication across a broad spectrum of component systems in a vehicle without implicating hardware or software upgrade within individual legacy systems and/or sensors. A universal translator is provided to interface between individual system components that exchange data in a seamless manner between legacy data formats and specific data formats advantageously employed by newly-developed, procured and installed individual component systems. One or more of an analog, digital or serial communications gateway network between one or more of vehicle control components and installed communication, navigation, surveillance and/or sensor sub-components and/or systems provides substantially seamless integration between such systems regardless of the individual data format and exchange capabilities to which the individual systems or sub-components may be designed.01-01-2009
20100030403METHODS AND APPARATUS FOR AIRBORNE SYSTEMS - In various representative aspects, an airborne delivery system according to various aspects of the present invention comprises a container and an autorotating rotor system. The container may contain contents, and the rotor system facilitates control of at least a portion of the flight of the airborne system and the descent. Exemplary features may include a guidance system, for example to guide and control the airborne system, and a wing for gliding.02-04-2010
20100030402LIGHT MULTI-PURPOSE AIRCRAFT WITH A CONTROLLING INTEGRATED COMPLEX - A light multi-purpose aircraft with a controlling integrated complex comprises a fuselage (02-04-2010
20120035788NAVIGATION AND CONTROL SYSTEM FOR AUTONOMOUS VEHICLES - A navigation and control system including a sensor configured to locate objects in a predetermined field of view from a vehicle. The sensor has an emitter configured to repeatedly scan a beam into a two-dimensional sector of a plane defined with respect to a first predetermined axis of the vehicle, and a detector configured to detect a reflection of the emitted beam from one of the objects. The sensor includes a panning mechanism configured to pan the plane in which the beam is scanned about a second predetermined axis to produce a three dimensional field of view. The navigation and control system includes a processor configured to determine the existence and location of the objects in the three dimensional field of view based on a position of the vehicle and a time between an emittance of the beam and a reception of the reflection of the emitted beam from one of the objects.02-09-2012
20120143406Aircraft Avionics System - An aircraft avionics system (06-07-2012
20090093918Control Arrangement - An aerospace control arrangement comprising a control unit connected to a plurality of connecting node sets, each connecting node set having associated therewith a plurality of connecting nodes, and each node having associated therewith at least one effecter and/or sensor, resulting in at least some of the nodes being connected to the control unit in a fault isolated star, point to point, arrangement.04-09-2009
20120215387TECHNIQUE FOR PROVIDING MULTIPLE UNDO AND REDO OPERATIONS FOR FLIGHT MANAGEMENT SYSTEMS - A technique for providing multiple undo and redo operations for flight management systems is disclosed. In one embodiment, in a method of providing multiple undo and redo operations for a flight plan in a flight management system, a temporary flight plan and a reference flight plan are created upon initiating a first revision on a created or default active flight plan. The temporary flight plan includes a copy of the active flight plan and the initiated first revision. The reference flight plan is a copy of the active flight plan. Further, multiple undo and redo functions are enabled upon initiating multiple revisions on the temporary flight plan for performing multiple undo and redo operations on the temporary flight plan.08-23-2012
20110137496METHOD AND APPARATUS FOR AUTOMATICALLY CONTROLLING AIRCRAFT FLIGHT CONTROL TRIM SYSTEMS - An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a tinier. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated. If the force sensor continues to sense a force after the tinier times for a predetermined time, the trim can he adjusted in the appropriate direction until the force sensor measures no significant pilot input force.06-09-2011
20100087969Automated System with Deterministic Response Times - The invention relates to an automated system, for example an aircraft flight management system (FMS). If proposes harmonizing the response times of the FMS system between the various scenarios of one and the same family, as and when the product, and its usage context, changes.04-08-2010
20090037036Automatic Control Systems for Aircraft Auxiliary Power Units, and Associated Methods - Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.02-05-2009
20100125380Method And Device For Fault Detection In The Load Path Of A Spindle Actuator - A method and a device for fault detection in the load path of a spindle actuator which is provided for actuating an aerodynamically active surface, in particular a high-lift flap of an aircraft, wherein the spindle actuator has a redundant load path which is formed by a spindle and a secondary connection which are connected rotationally fixedly to one another on the driven side and are coupled to the surface to be actuated and which are assigned separate load paths on the drive side, whereof the primary load path contains a primary spindle which is driven by a motor and can be fixed in its rotational movement by a primary brake, and the secondary load path contains the secondary inner connection, which is in particular arranged concentrically in the primary spindle, which can be fixed in its rotational movement by a secondary brake, in which output signals representing the turning position of the spindle, which are generated by means of at least one turning position sensor which is coupled to the primary spindle on the drive side, are detected and evaluated, wherein: fixing the secondary connection in its rotational movement is achieved by means of the secondary brake; the redundant load path is put under load, when the primary brake is released, the load being applied via a predefined torque by the motor as far as the secondary brake is fixing the secondary connection; and the detection of a fault is evaluated when a change in the turning position, which lies outside the tolerance range predefined for an intact spindle actuator, is detected at the turning position sensor coupled to the primary spindle.05-20-2010
20100125379Device Allowing Improvement in Maintenance Procedures for Onboard Equipment - The present invention relates to the field of aiding ground maintenance of an aircraft. More particularly, the invention consists of a portable access terminal intended to aid maintenance, commonly designated by the acronym PMAT for Portable Maintenance Access Terminal.05-20-2010
20100125378AUTOMATIC THROTTLE ROLL ANGLE COMPENSATION - A method, apparatus, and computer program product for adjusting a thrust for an aircraft. A level of thrust is dynamically identified using a drag on the aircraft needed to substantially maintain a speed of the aircraft in a turn to form an identified level of thrust during turning of the aircraft. The turn of the aircraft is performed using the identified level of thrust.05-20-2010
20120143405DATA SYNCHRONISATION FOR A FLIGHT INFORMATION SYSTEM06-07-2012
20080312777Automatic Strategic Offset Function - Embodiments of methods and systems for providing an automatic strategic offset function are disclosed. In one embodiment, a method for enhancing the collision avoidance capability of an aircraft includes determining a flight plan, determining a boundary for the flight plan, generating a variable offset from the flight plan that is within the boundary, the variable offset including a lateral offset distance, and navigating an aircraft based on the variable offset.12-18-2008
20100280682METHOD FOR ACTIVE POWER MANAGEMENT AND ALLOCATION OF FUNCTIONALITY - Methods for active power management, i.e., the power management method may be activated in response to changes in the supply and demand of power in a system, are disclosed. The power management method may use dynamically collected data reporting levels of electrical power utilized by systems while matching them to the available power. One embodiment of the present invention may be applied in smaller or medium sized systems. Another embodiment of the present invention may be implemented making use of additional aircraft resources, such as an integrated modular avionics (IMA) line replaceable unit (LRU) in larger sized systems. Both of these embodiments may make use of data collected from systems utilizing or generating electrical via the bus power control unit (BPCU) LRU, the data processing taking place either locally in the BPCU (small or medium sized systems) or in the IMA (larger systems).11-04-2010
20110270471Control Panel For An Aircraft - The control panel (11-03-2011
20080208396Mission Control System and Vehicle Equipped with the Same - There is described a mission control system having an operator seat; a head-mounted display and digital gloves worn by the operator; a headset having a microphone and integrated in the head-mounted display; a tracker for tracking the movements of the head-mounted display and the digital gloves; and a mission computer housed in the operator seat and connected to the head-mounted display, to the digital gloves, to the headset, to the microphone, and to the tracker, to allow the operator to impart gestural commands by means of the digital gloves, and voice commands by means of the microphone, and to receive visual information by means of the head-mounted display, and audio information by means of the headset.08-28-2008
20080208397LOGISTICS SYSTEM TO SUPPORT DEPLOYED ASSETS WITH OVER THE HORIZON CONNECTIVITY - A logistic systems to support deployed platforms that includes a reporting system located within deployed assets, an over-the-horizon (OTH) communication system, an information distribution node, a logistics control system, and a servicing activity. The reporting system located within deployable assets monitors and reports deployed asset status information using the OTH communication system. Thus, the reporting system passes deployed asset status information to the logistics controller via the information distribution node. The logistics controller receives deployed asset status information and allocates the necessary resources to service the deployed asset based on received deployed asset status information. This allocation of resources is coordinated at the servicing activity or service depot in communication with the logistics controller prior to the arrival of the deployed asset saving valuable time.08-28-2008
20090118874Systems and methods for controlling aircraft electrical power - Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.05-07-2009
20090276106Multiple Telemetry Stream Parsing and Reconstruction System - The invention generally relates to a telemetry system and method for parsing a set of archived telemetry streams for the purpose of reconstructing the data contained within the set of archived telemetry streams into a newly constructed set of telemetry streams. The newly constructed set of telemetry streams are used as a set of test driver data to evaluate performance in variety of ground based systems. The availability of test drivers produced by the preferred embodiment of the invention shortens the system development time line by allowing an evaluation of hardware and software changes ahead of the actual delivery of vehicle telemetry components, resulting in a reduction of overall program costs.11-05-2009
20090281683Developments in or relating to system prognostics - A method of mitigating the system-level effect of a fault detected in a vehicle system during a vehicle mission, the method comprising: using a processor to automatically prognose the system-level effect of said fault in terms of the residual capability of the vehicle system during the remainder of the mission, on the basis of predetermined stored data; using a processor to automatically generate a corresponding set of alternative reversionary or investigative action plans for mitigating said system-level effect during the remainder of the vehicle mission, on the basis of said prognosis; submitting the set of alternative reversionary action plans to a decision-making authority for determination by the decision-making authority of a preferred one of the reversionary action plans suitable for achieving a mission objective; and using a control unit, operably connected to the vehicle system, to implement the preferred reversionary action plan in accordance with said determination.11-12-2009
20110172853METHOD AND DEVICE FOR ATTENUATING THE EFFECTS OF TURBULENCE ON AN AIRCRAFT - A method for attenuating effects of turbulence on an aircraft, and a device to implement the method, the method including: using at least one signal on a wind profile signal, along an excitation direction, representing, at a given moment in an aircraft referential, a component along the excitation direction of the wind speed at a front of the aircraft according to a distance along a longitudinal direction of the aircraft; carrying out a frequency determination, in which the wind profile signal is processed to determine a frequential content; and selecting a control strategy to be adopted according to the previously determined frequential content, the strategy enabling at least one applicable control law to be identified.07-14-2011
20090287364VISUAL AIRCRAFT SPACING TOOL - An air traffic display aid and method that uses parameters for defining a heading for an alpha approach and a beta approach. These can be intersecting or converging runways, dependent or independent parallel runways or airways in en-route configurations. A target reference point is determined in dependence upon the alpha and beta approaches. And an image reference point is determined in dependence upon at least one of the target reference point, a difference between the headings, a characteristic of the beta approach and an offset. Single target mirror ghosting, in-trail ghosting on demand, associated configurations and user selectable resynchronization spacing is also supported.11-19-2009
20090292407SOLAR-POWERED AIRCRAFT WITH ROTATING FLIGHT SURFACES - A solar-powered aircraft having a rotating tail assembly and/or a fore assembly is provided. The tail and fore assemblies have solar cells mounted on their upper surfaces and are rotated during flight to track the sun.11-26-2009
20100131124METHODS AND SYSTEM FOR TIME OF ARRIVAL CONTROL USING TIME OF ARRIVAL UNCERTAINTY - Methods and a system for vehicle control are provided. The system includes an input device configured to receive a required time of arrival at a waypoint and a processor communicatively coupled to the input device. The processor is programmed to determine a forward late time profile, determine a forward early time profile representing the earliest time the vehicle could arrive at a point along the track and still arrive at the waypoint while transiting at a maximum available speed, and determine an estimated time uncertainty (ETU) associated with at least one of the forward late time profile and the forward early time profile. The system also includes an output device communicatively coupled to the processor, the output device configured to transmit the determined uncertainty with a respective one of the at least one of the forward late time profile and the forward early time profile to a display05-27-2010
20110270470AIRCRAFT SYSTEMS AND METHODS WITH ACTIVE DECELERATION CONTROL - A system is provided for controlling the speed of an aircraft during a deceleration segment between a first state associated with a first speed and a first time and a second state associated with a second speed and a second time. The system includes a navigation system configured to determine the first state; a guidance system configured to determine the second state; and an active deceleration system coupled to the navigation system and the guidance system and configured to construct the deceleration segment between the first state and the second state with at least one intermediate speed between the first speed and the second speed.11-03-2011
20120296497UNMANNED AERIAL VEHICLE AND METHOD FOR CONTROLLING THE UNMANNED AERIAL VEHICLE - In a method for controlling an unmanned aerial vehicle (UAV), a digital image is obtained by an image capturing device of the UAV. The method detects an object in the digital image, determines a distance between the detected object and the UAV, and obtains a flight direction of the UAV if the distance is less than a preset value. The method further calculates a relative position and a relative angle between the detected object and the UAV, determines a flight limiting range of the UAV according to the relative position and the relative angle, and controls the flight direction of the UAV according to the flight limiting range.11-22-2012
20120296499DEVICE AND A METHOD FOR CONSTRUCTING A FLIGHT PATH IN ORDER TO REACH A DESTINATION11-22-2012
20120290153FLIGHT CONTROL SYSTEM WITH ALTERNATE CONTROL PATH - A flight control system and method including a primary flight control path between one or more pilot controls and control surface actuators on an associated aircraft, wherein the primary control path includes one or more flight control computers and one or more first data concentrators; and a secondary flight control path between the one or more pilot controls and the control surface actuators, wherein the secondary flight control path utilizes direct mode control laws to control the control surface actuators; wherein the primary flight control path and the secondary flight control path are independent from each other and the secondary flight control path is operative upon detection of a fault in the primary flight control path.11-15-2012
20120290154PROVIDING DATA FOR PREDICTING AIRCRAFT TRAJECTORY - The present invention provides a system and method of producing a description of the flight intent of an aircraft expressed using a formal language. The description may be used to generate a predicted aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to express the flight intent of the aircraft in a formal language. The flight intent describes a flight in terms of flight segments, and provides information of the path to be flown and how it is to be flown. The flight intent does not necessarily define unambiguously the aerodynamic configuration of the aircraft and the motion of the aircraft during the flight. The flight intent is used alongside other information to generate the aircraft intent that does describe unambiguously the aircraft's trajectory.11-15-2012
20100145554 DEVICE AND METHOD FOR AUTOMATICALLY GENERATING A CONTROL ORDER FOR AN AIRCRAFT CONTROL SURFACE - A device and a method for automatically generating a control order of an aircraft control surface06-10-2010
20080249671Method and Device For Providing an Multi-Engine Aircraft Pilot With Data Concerning Said Engines - The invention concerns a device (10-09-2008
20080249670Method and Device for Carrying Out at Least One Flight Testing on an Aircraft and the Use Thereof - The inventive device (10-09-2008
20080249669Device at an airborne vehicle and a method for collision avoidance - A device at an airborne vehicle including a flight control system configured to control the behaviour of the airborne vehicle based on acceleration commands, a first control unit configured to provide the acceleration commands to the flight control system, and a collision avoidance unit. The collision avoidance unit includes a detection unit arranged to detect whether the airborne vehicle is on a collision course and a second control unit arranged to feed forced acceleration commands to the flight control system upon detection that the airborne vehicle is on a collision course. A method for collision avoidance in an airborne vehicle.10-09-2008
20120296498METHOD FOR CONTROLLING THE DECELERATION ON THE GROUND OF A VEHICLE - The invention relates to a method for controlling the deceleration on the ground of a vehicle. The method obtains, from the crew of the vehicle or from an outside operator, parameters relating to its current position and its current speed. Then it determines a reference position and speed of the vehicle, the reference position being a theoretical position to be reached by the vehicle. Finally it determines, from indicated parameters and from reference parameters, a deceleration command with a view to ending up at a target position at a preselected speed.11-22-2012
20080275597BALANCING THE POWER OF TWO TURBOSHAFT ENGINES OF AN AIRCRAFT - The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M11-06-2008
20080288130SYSTEM FOR SELECTING DATA REPRESENTING AN AIR PARAMETER, PROCESS AND COMPUTER PROGRAM RELATING TO THE SAME - A system for selecting a datum among a set of data representing an air parameter, this set comprising at least two engine data obtained by measurement respectively in the zone of two engines of an aircraft and at least two reference data obtained by measurement in the zone of the fuselage of the aircraft, the system comprising: 11-20-2008
20080294303Onboard execution of flight recorder application - An apparatus in an example comprises an onboard controller and a flight recorder application. The onboard controller is onboard a vehicle and comprises an onboard operating system (OS). The flight recorder application is executable onboard the vehicle by the onboard operating system.11-27-2008
20080294306METHOD AND DEVICE FOR MONITORING A POSITION INDICATION OF AN AIRCRAFT - The device (11-27-2008
20080294304Method for Optimizing a Fuel Consumption of an Aircraft During the Flight Thereof - The invention relates to a method for optimizing the fuel consumption of an aircraft during flight. At a given point of the flight, a fuel excess (EXTRA) is determined relative to the statutory loads depending on the flight profile and weather conditions forecast for the rest of the flight. If the excess (EXTRA) is less than a given value (EXTRA-mini), for at least one of the forthcoming flight phases (11-27-2008
20080312776METHOD AND APPARATUS FOR MANAGING FLIGHT PLANNING - A computer implemented method, apparatus, and computer usable program code for displaying flight plan data. First level flight plan data is displayed and user input is received selecting a selection of a portion of the first level flight plan data. In response to receiving the selection of the portion of the first level flight plan data, second level flight plan data is displayed, wherein the second level flight plan data displayed is used to derive the selected portion of the first level flight plan data selected by the user input.12-18-2008
20090265049AIRCRAFT SYSTEM EMISSIONS AND NOISE ESTIMATION MECHANISM - A method for generating emissions estimations of an aircraft is provided. A plurality of aircraft parameters is gathered. A first parameter of the plurality of aircraft parameters is selected for a first model. The first model mathematically contributes to the formulation of a first emissions estimation. The first model is considered with a plurality of additional models in view of the plurality of aircraft parameters to obtain the first emissions estimation. The first emissions estimation is a composite representation of the first model and the plurality of additional models in view of the plurality of aircraft parameters.10-22-2009
20100324758Compound Aircraft Control System and Method - The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of operational objectives each of which is designed to achieve any particular command.12-23-2010
20090312891Conversion system fault management system for tiltrotor aircraft - The difference between a first position of a first pylon of a tiltrotor aircraft and a second position of a second pylon of the aircraft is prevented from becoming too large. An actuator position error for the first pylon is calculated from a difference between the first position and a commanded first position of the first pylon. An actuator position error for the second pylon is calculated from a difference between the second position and a commanded second position of the second pylon. An absolute value of the actuator position error for the first pylon is compared to the preset limit. If the absolute value of the actuator position error for the first pylon is greater than or equal to a preset limit, the actuator position error for the second pylon is calculated from the difference between the first position and the second position.12-17-2009
20120296496UPGRADED FLIGHT MANAGEMENT SYSTEM AND METHOD OF PROVIDING THE SAME - A preexisting FMS system may be upgraded to increase its functionality while still taking advantage of certain components of the legacy system previously provided on the aircraft and replacing other preexisting components with different components for enhancing the functionality of the FMS system. The preexisting IRU, CADC, DME receiver and DFGC in the upgraded FMS system are in communication with the legacy AFMC but, instead of employing the legacy EFIS which existed in the preexisting FMS system, the EFIS is replaced by a data concentrator unit as well as the display control panel and integrated flat panel display, and a GPS receiver. The upgraded FMS system is capable of such increased functionality as increased navigation database storage capacity, RNP, VNAV and RNAV capability utilizing a GPS based navigation solution, and RTA capability, while still enabling the legacy AFMC to exploit its aircraft performance capabilities throughout the flight.11-22-2012
20080208398Energy Protecting Device for Aircraft - The invention concerns a device (08-28-2008
20120059535SYSTEMS AND METHODS FOR RTA CONTROL OF MULTI-SEGMENT FLIGHT PLANS WITH SMOOTH TRANSITIONS - Methods, systems and device are provided for smoothing a required time of arrival (RTA) speed transition for an aircraft in a multi-segmented speed profile including at least one preceding region with a first predetermined speed pad and at a speed constrained region with a second predetermined speed pad. Exemplary methods include, but are not limited to determining whether a speed constrained region is engaged by a preceding region based at least in part on a speed of an aircraft. If the speed constrained region is engaged, the instructions determine a revised second speed pad for the speed constrained region. If the speed constrained region is not engaged then the instructions assign a default speed pad as the second speed pad for the speed constrained region. The instructions also compile a new speed profile that is defined by one of the revised second speed pad and the default speed pad for the speed constrained region and transmit commands that accelerate the aircraft to a new speed based on the new speed profile.03-08-2012
20080269962Method and a system for determining and indicating a sound nuisance level outside an aircraft - A method of determining a sound nuisance level outside an aircraft, in which method: 10-30-2008
20090157237MANUAL SELECTION OF THE ACTIVE REFERENCE OF A FLIGHT PLAN FOR THE GUIDANCE OF AN AIRCRAFT - The present invention relates to a method allowing a modification of the flight plan of an aircraft in a semi-automated manner. The invention presents the main advantage of affording the crew of an aircraft a method for aiding the rejoining of a flight plan requiring only a designation by an operator of the new active reference that he wishes to use for guiding the aircraft.06-18-2009
20100145553METHOD AND DEVICE FOR SHARING DATA BETWEEN ON-BOARD SYSTEMS IN AN AIRCRAFT - The object of the invention is in particular a method and a device for exchanging data between a technical management system of an aircraft and a mission management system of the said aircraft, in order to permit one of the said systems to determine the consequences of an event detected in the other of the said systems. After at least one event has been detected (06-10-2010
20100274417System and Method of Interaction and Holistic Representation of Tasks - The general field of the invention is that of viewing systems comprising first means making it possible to process and to store the various data necessary for the accomplishment of a technical or industrial process, second means making it possible to determine the various tasks to be accomplished by a user in the course of the process on the basis of the previous data, a computer for generating graphical images associated with a viewing device and a man-machine interface with the said viewing device. The viewing device according to the invention displays a succession of graphical icons, each icon representing a task to be accomplished, the various icons being ordered according to a time scale extending from the start to the end of the process. The system and the method according to the invention are of global or holistic types. A certain number of operations on these icons can be performed by means of the man-machine interface. The favoured field of the invention is that of aircraft instrument panels.10-28-2010
20090030563Systems And Methods For Providing Localized Heat Treatment Of Metal Components - Systems and methods for defining information provided by aircraft are provided. An exemplary method, involving an aircraft that is operative to provide information in a first report format, includes: communicating information corresponding to a second report format definition to the aircraft, wherein the information corresponding to the second report format definition is received at the aircraft via wireless communication; and receiving, from the aircraft, information complying with the second report format definition.01-29-2009
20090125166ACTIVE USER INTERFACE HAPTIC FEEDBACK AND LINKING CONTROL SYSTEM USING EITHER FORCE OR POSITION DATA - A system and method are provided for supplying haptic feedback to, and for electronically linking, pilot and co-pilot user interfaces. The user interface haptic feedback and linking are implemented using either force or position data. If the force or position data become unavailable, then position or force data, respectively, are used to implement the user interface haptic feedback and linking.05-14-2009
20090182462Method and system to accelerate aircraft wheels before touch-down - This invention improves the previous art to accelerate an aircraft's wheels before landing to avoid skidding in that it shows how to (1) provide adequate power by using the compressed air and gases of the jet engine, (2) rely on existing information from onboard systems to precisely control wheel spin and (3) integrate the propulsion device into the wheel structure. The invention minimizes the additional weight necessary to rotate the wheels of a landing aircraft, limits the aerodynamic impact and allows the use of existing tires without modifications.07-16-2009
20090132102ACTUATOR CONTROL REDUCING THE LEVEL OF VIBRATION OF AN ASSOCIATED FLEXIBLE STRUCTURE - The aim of the method of controlling at least one mechanical system exhibiting at least one flexible structure element and at least one actuator or group of actuators is to reduce the level of vibrations of said element while controlling the actuator or group of actuators in such a way as to achieve at least one objective assigned to the mechanical system. The control consists of increments having to be carried out at a sampling period T, each of the increments being constant in amplitude in a sampling time interval extending between two successive sampling instants and each of the increments being applied during a duration which is less than or equal to the sampling period T. In each sampling interval, at least one of the initial and final instants of application of the increment is modified by adding a variable, random or pseudo-random, temporal deviation dT.05-21-2009
20090138141VEHICLE HEALTH MONITORING SYSTEM ARCHITECTURE FOR DIAGNOSTICS AND PROGNOSTICS DISCLOSURE - A health monitoring system for a vehicle system includes an operational support system including a plurality of managers and a decision support module. Each manager corresponds to a different sub-system of the vehicle system, and comprises a plurality of reasoners and a fusion block. Each reasoner is configured to obtain data and provide preliminary output regarding a different component of the sub-system based on the data. The fusion block is coupled to the plurality of reasoners, and is configured to receive the preliminary output and generating manager output based on the preliminary output. The decision support module is coupled to the plurality of managers, and is configured to receive the manager output and provide a decision support output based on the manager output.05-28-2009
20090138138IMAGING AND DISPLAY SYSTEM TO AID HELICOPTER LANDINGS IN BROWNOUT CONDITIONS - An imaging and display system provides helicopter pilots with an unobstructed display of a landing area in a brownout or whiteout condition by capturing a high resolution image of the landing area prior to obscuration. Using inertial navigation information from the aircraft or an independent system, the system transforms the image to a desired viewpoint and overlays a representation of the helicopter's current position relative to the landing area. The system thus greatly improves orientation and situational awareness, permitting safe and effective operation under zero visibility brownout conditions.05-28-2009
20090138139TECHNICAL DATA NAVIGATION SYSTEM AND METHOD - The present invention is directed to a technical data navigation system and method that provides a single point of access search, retrieve and aggregate vehicle post delivery technical data via a lightweight three-dimensional (3D) navigational interface. The system and method provide for a streamlined process of virtually locating and identifying parts on a vehicle. The system and method further provide for a single point for interaction of delivering 3D simulations.05-28-2009
20090138140VEHICULAR LINEAR SENSOR SYSTEM - Vehicular sensor systems are provided. The vehicular sensor systems includes a support, first, second, and third sensors, and a support actuator. The first sensor is coupled to the support and configured to rotate about a first sensor axis. The first sensor has a first field of detection with a first central axis. The second sensor is coupled to the support and configured to rotate about a second sensor axis. The second sensor has a second field of detection with a second central axis. The third sensor is coupled to the support and configured to rotate about a third sensor axis. The third sensor has a third field of detection with a third central axis. The support actuator is coupled to the support and configured to rotate the support about a support axis. The first, second, and third central axes are substantially within a plane.05-28-2009
20090005918METHOD FOR OPTIMIZING THE EXIT OF AN AIRCRAFT IN A HOLDING CIRCUIT - The method of optimizing the exit of an aircraft traversing for a known duration (D) a holding circuit forming a racecourse comprising two parallel branches of the same distance, the branches being traversed in a first time (t01-01-2009
20090143925ROBUST CONTROL EFFECTOR ALLOCATION - Method and apparatus is disclosed which allocates the execution of a commanded vehicle maneuver among the vehicle's control effectors capable of affecting such maneuver, with consideration given to the possible nonlinear and/or non-monotonic effects each control effector's displacement may have on the vehicle and on each other's performance.06-04-2009
20090143926Method and apparatus for tracking center of gravity of air vehicle - The method and apparatus for tracking a center of gravity (COG) of an air vehicle provides a precise calculation and updating of the COG by disposing a plurality of acceleration measuring devices on a circumference of one or more rings in a manner that establishes redundancy in acceleration measurement. A multivariable time-space adaptive technique is provided within a high speed digital signal processor (DSP) to calculate and update the position of the COG. The system provides the capability of executing a procedure that reduces dispersion in estimating angular velocities and lateral accelerations of a moving vehicle and corrects the vehicle's estimated angular velocities and lateral accelerations. In addition, a consistency check of the measured values from the acceleration measuring devices is performed to assist in fault detection and isolation of a faulty accelerometer in the system.06-04-2009
20090259350PISTON ENGINE AIRCRAFT AUTOMATED PRE-FLIGHT TESTING - One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.10-15-2009
20090326740Methods for determining an initial AINS heading - Two methods for determining a best initial heading estimate for use in an AINS system, while recording position data values and in-motion data values, assigning incremental changes to indexed heading ψ12-31-2009
20090326739METHOD AND DEVICE FOR DETECTING OSCILLATORY FAILURES RELATED TO A SERVOCONTROL SUBSYSTEM OF AN AIRCRAFT CONTROL SURFACE - Method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain.12-31-2009
20090326738DEVICE FOR AIDING TO TAKE A DECISION CONCERNING THE ABILITY OF AN AIRCRAFT TO START A FLIGHT - The device (12-31-2009
20090326737SMART HYBRID ELECTRIC AND BLEED ARCHITECTURE - An aircraft architecture may be designed to create an optimal balance between electric power and bleed power in order to match or improve current more electric architecture (MEA) performance while simplifying power extraction from the engines as well as simplifying the electrical system. Conventional aircraft architectures may use electric only ECS and cabin pressurization systems (so-called “no bleed” systems). Alternatively, older conventional aircraft may use strictly engine bleed air to provide power for ECS and cabin pressurization systems. The present invention, on the other hand, provides an architecture which may optimize the use of both engine bleed air and MEA designs to provide a system that may be simpler and potentially more reliable and available as compared to conventional aircraft architectures.12-31-2009
20090326736Relative navigation for aerial refueling of an unmanned aerial vehicle - A method and system for navigating an unmanned aerial vehicle (UAV) for aerial refueling is described. A system processor in the UAV receives navigation data from a tanker aircraft and calculates a plurality of relative navigation solutions with respect to the tanker aircraft. The system processor compares the plurality of relative navigation solutions to identify any inconsistent solutions. The inconsistent solutions are discarded and the system processor navigates the UAV in position for refueling using the remaining relative navigation solutions.12-31-2009
20080306638METHOD AND DEVICE TO ASSIST IN NAVIGATION IN AN AIRPORT SECTOR - The invention relates to a method and device to assist in navigation in an airport sector. The inventive method and device make it possible to automatically calculate the points of intersection between the path of the flight plan and the zones having speed limitations all around an airport and calculate a speed profile conforming to these limitations. The inventive method and device also make it possible to use an automatic guidance automatically defining flight instructions corresponding to the calculated speed profile. Furthermore, the invention calculates predictions concerning the flight parameters.12-11-2008
20080306637BATTERY NETWORK SYSTEM WITH LIFE-OPTIMAL POWER MANAGEMENT AND OPERATING METHODS THEREOF - A system and methods for life optimal power management of a distributed or centralized battery network system for use in aircraft functions and subsystems are disclosed. The method determines power priority of the subsystems, and selectively distributes power from the battery network system to the subsystems based on the power priority. Concurrently with distributing power, the method manages the energy in the battery network system. To determine whether the battery power is sufficient for aircraft functions, the method also computes and indicates the actual available energy left in the battery network systems. With this approach, the system and methods can provide a persistent power supply in the event an unexpected battery failure occurs, thereby enabling the aircraft to safely maintain flight operability despite a battery failure.12-11-2008
20090198392APPARATUS, PROGRAM PRODUCT, AND METHODS FOR UPDATING DATA ON EMBEDDED CONTROL SYSTEMS - Embodiments of the present invention provide an augmentation apparatus, program product, and methods for providing updated mission control data to an embedded control system of an aircraft or other vehicle. This augmentation can include a mission system interface unit, a user interface unit, and a display unit. The mission system interface unit can interface with the embedded control system and can exchange data and control signals with the embedded control system. The user interface unit can couple to the mission system interface unit and the display unit to provide a user a direct interface with embedded control system and to supplement the displays of the embedded control system.08-06-2009
20090198393METHOD AND APPARATUS FOR LOADING SOFTWARE AIRCRAFT PARTS - A computer implemented method, apparatus, and computer usable program code for managing a software aircraft part. A computer implemented method identifies an aircraft from a set of target aircraft to form a target aircraft. Software for use in the aircraft is identified. A determination is made as to whether compatibility exists between the software and the target aircraft. The software aircraft part is created comprising the software and metadata relating usability of the software aircraft part in the target aircraft in response to a determination that compatibility exists between the software and the target aircraft.08-06-2009
20110144834MODULAR ARTICULATED-WING AIRCRAFT - Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.06-16-2011
20110144832MULTIPLE TRANSITION RNP APPROACH PROCEDURE - A required navigation performance (RNP) approach method is described that includes providing a plurality of fixed, predetermined waypoints associated with at least one runway of at least one airport, providing a predetermined plurality of constant radius turnpoints connecting a downwind leg of the runway to a final approach leg of the runway, and assigning one of the constant radius turnpoints to an aircraft capable of flying an RNP approach, the turnpoint selected to provide separation from other approaching aircraft and a landing time for the aircraft.06-16-2011
20090204277Method of Estimating Atmospheric Data at Any Point of a Path of an Aircraft - The subject of the present invention is a method of estimating, at any point of a path of an aircraft, characteristics of the wind making it possible to take very close account of the winds to construct predictions of the times of passage and of the consumption of the aircraft along its flight plan, and this method is characterized in that it consists in collecting, around the trajectory of the aircraft, a grid of parameter values of winds at a predetermined number of points in space, in comparing these values to those deriving from space-time wind trend models, in selecting, path section by section, the most likely model, and in interpolating, for each section, the local characteristics of the wind of all the points of interest of the trajectory.08-13-2009
20110231036AIRCRAFT COMMUNICATIONS RADIO TUNING AID SYSTEM AND METHOD - Methods and apparatus are provided of displaying air traffic control communication information in an aircraft having an aircraft communications radio. Each air traffic control (ATC) communication station that is within a predetermined distance of an aircraft position is identified. Indicia representative of the identified ATC communication stations that are determined to be within the range of the aircraft communications radio are rendered on a display device.09-22-2011
20120078449AUTOMATICALLY AND ADAPTIVELY CONFIGURABLE SYSTEM AND METHOD - Methods and apparatus are provided for automatically and adaptively configuring a system for a user. User data that includes information representative of temporal and contextual user preferences, behaviors, habits, biases, idiosyncrasies, and tendencies associated with system settings and configurations are loaded into the system. The system is then configured based on the user data. User-initiated operations of the system are continuously monitored to model user performance. The user data are continuously updated based on the modeled user performance, and the system is continuously and automatically reconfigured based on the updated user data.03-29-2012
20120078448MIXED-INTIATIVE TRANSFER OF DATALINK-BASED INFORMATION - A system and method are provided for transferring datalink-based information into an aircraft flight management system. When a datalink message is received in an aircraft, it is parsed into individual information elements. The operational impact of the received datalink message on the aircraft is determined from the individual information elements. A method of supplying pilot feedback regarding the received datalink message is determined from the determined operational impact. The pilot feedback regarding the received datalink message is supplied using the determined method. At least selected portions of the individual information elements are selectively transferred into the aircraft flight management system (FMS).03-29-2012
20120078447AUTOMATIC PRESENTATION OF A SHORTCUT PROMPT TO VIEW A DOWNLINK REQUEST MESSAGE RESPONSIVE TO A CONFIRM-RESPONSE MESSAGE - A system to reduce head-down time for a flight crew is provided. The system includes a functional module including a set of screens used to receive and send controller pilot data link communications (CPDLC) messages between an aircraft and a ground system; a message composition screen communicatively coupled to the functional module; and a shortcut interface communicatively coupled to the functional module, wherein a shortcut prompt is automatically displayed when a confirm-response message received responsive to a previously-sent downlink request message is viewed, and wherein the previously-sent downlink request message is displayed when the shortcut interface is implemented.03-29-2012
20120078446Integrated Upsampler and Filtering for Multi-Rate Controller for Electro-Mechanical Flight Actuation System - Presented is a system and method for controlling an actuator in a multirate control system using an integrated upsampler and filter, comprising an incremental command limiter for changing a command from a first control system into a limited incremental command in a second control system, a lead-lag filter for filtering the limited incremental command to attenuate high frequencies, and a feed forward path for reducing phase loss in rate output signal at low frequencies. In embodiments, a command position signal received at the sampling rate of the first control system is interpolated into incremental command position signals at the sampling rate of the second control system. Position error signals and rate error signals from the devices being controlled are used as feedback to further stability the control loops.03-29-2012
20120078445COMPUTER ASSISTED HUMAN MACHINE INTERFACE DISPLAY - Methods and apparatus are provided for selectively balancing pilot workload. The apparatus comprises a display device configured to display a user interface (UI) and a processor. The processor is configured to determine a state of the pilot and/or a state of the aircraft, prepare modification to the UI based in part on the state of the pilot and/or the state of the aircraft such that the modification adds one or more command icons without obscuring, without removing, and without replacing any information item on the display, and to execute the modification.03-29-2012
20080262663METHOD FOR MONITORING PLANE ENGINES - A method for monitoring plane engines The present invention relates to a method for monitoring engines of a plane comprising at least two engines (m10-23-2008
20090210104PROCESS AND DEVICE FOR DIAGNOSTIC AND MAINTENANCE OPERATIONS OF AIRCRAFT - The object of the invention is a method and a device for filtering diagnostic messages obtained from a plurality of elements of a system, each of these elements comprising diagnostic means capable of detecting a failure and of transmitting a message comprising at least one failure indication. The state of at least certain elements of the said plurality of elements is represented by a model of state. After at least one failure message has been received, this message is filtered according to the failure indication that it contains and according to the model of state. In response to the filtering step, the model of state is updated according to the failure indication or the message is rejected. The filtering step is advantageously based on a propositional logic mechanism.08-20-2009
20090254230Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations - An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including: 10-08-2009
20090248224Integrated Air Navigation and Flight Control System - A method and a device for solving air traffic congestions, improve safety, and reduce faults to simplify cockpit equipment. The method serves the navigation of airplanes from port to port with the help of GPS signals. The navigation support is based on digital maps and position control by GPS signals, which GPS signals are corrected by GPS reference signals wherein depending on the present position and state of motion of the airplane the map is respectively the movement is selected automatically from a library and shown on a screen.10-01-2009
20100152928SYSTEM FOR SECURING THE DISPLAY OF INSTRUCTIONS ORIGINATING FROM AIR TRAFFIC CONTROL - The system for automatically registering flight instructions for aircraft comprises a flight computer delivering a first set of flight instructions defining a pre established flight plan, called CONS_FMS, the system comprising a display, the display representing the current flight instructions, the system comprising a device for controlling instructions which comprises means of adjusting a second set of flight instructions, called CONS_PILOTE, the system comprising a manager of instructions originating from air traffic control, the instructions being transmitted by means of a data link, said instructions defining a third set of instructions, called CONS_CONTROLEUR.06-17-2010
20100152923DYNAMIC DISPLAY OF NAVIGATIONAL INFORMATION - A display system for dynamically displaying aircraft flight information. The system includes a processor, memory, and a display. The processor is capable of communicating with the memory, the display, and a system environment of the aircraft. The processor is configured to display a flight map for the aircraft on the display, to evaluate state variable(s) dynamically representing state(s) in the aircraft system environment, and dynamically modify the flight map based at least in part on the evaluation.06-17-2010
20100174423METHOD AND A SYSTEM FOR AUTOMATICALLY MANAGING CHECK LISTS ON AN AIRCRAFT - A method and a system for automatically managing check lists on an aircraft.07-08-2010
20100262319METHODS AND SYSTEMS FOR DISPLAYING ASSISTANCE MESSAGES TO AIRCRAFT OPERATORS - Methods and systems for displaying assistance messages to aircraft operators are disclosed. A method in accordance with one embodiment includes receiving an input from an aircraft operator at an aircraft flight deck, comparing a characteristic of the input to at least one target value for the characteristic, and, if the characteristic of the input differs from the at least one target value for the characteristic by at least a threshold amount, displaying an assistance message to the aircraft operator. The assistance message can include a complying input and/or an instruction for creating a complying input. The input and the assistance message can be displayed simultaneously.10-14-2010
20100161156DEVICE FOR ASSISTING IN THE CHOICE OF A DIVERSION AIRPORT - The invention relates to a device for assisting in the choice of a diversion airport for an aircraft piloted by a crew (06-24-2010
20100161154OPERATIONS SUPPORT SYSTEMS AND METHODS WITH POWER MANAGEMENT - A power management system includes a data fusion unit configured to receive first health indicators from an engine diagnostics module and second health indicators from a power assurance module. The data fusion unit is configured to data fuse the first and second health indicators. A power assessment and decision support unit is coupled to the data fusion unit and configured to generate power available based on the fused first and second health indicators. A system diagnostic reasoner unit is coupled to the data fusion unit, and configured to provide a system level fault diagnosis based on the fused first and second health indicators. A graphical user interface is coupled to the power assessment and decision support unit and the system diagnostic reasoned unit. The graphical user interface is configured to display the system level fault diagnosis and the power available.06-24-2010
20100168935METHOD OF AND SYSTEM FOR MAINTAINING OPERATING PERFORMANCE OF A TRANSPARENCY - Repair or replacement of a transparency mounted in body of a vehicle, e.g. an aircraft when one or more properties of the transparency is (are) operating outside of an acceptable limit(s) is arranged by monitoring operating performance of a property of the transparency, e.g. by mounted a sensor, e.g. a sensor for detecting moisture; a sensor for detecting impacts and vibrations; a sensor for detecting fractures; a sensor for detecting electric arcing, and a sensor for measuring temperature of an electrically conductive coating, on the transparency. Scheduling repair or replacement of the transparency at a geographical area when the operating performance of the property is outside an acceptable operating performance limit, and forwarding the schedule to the vehicle and to a maintenance location to prepare for the repair or replacement of the transparency at the geographical work area.07-01-2010
20080215193ELECTRONIC FLIGHT BAG HAVING FILTER SYSTEM AND METHOD - A system and method for filtering information from an electronic flight bag system (EFB) used on a mobile platform, for example, on an aircraft. In one embodiment the system makes use of an EFB having a display with a selection to enable a filter. When the filter is enabled, the user is presented with a plurality of options for limiting retrieved information to only specific types of information or data. This allows one, two or more layers of filtering to be implemented on the information that is searched and obtained from the EFB, and enables a limited subset of information to be obtained that is available for viewing on a display associated with the EFB. The system and method eliminates or significantly reduces the amount of non-relevant information that the crew members are required to review when attempting to obtain specific types of information from the EFB.09-04-2008
20100217459Method for Aiding the Formulation of the Speed Strategy of an Aircraft with a View to Adhering to a Time Constraint - The invention relates to a method for formulating the strategy of an aircraft, with a view to favouring adherence to a time constraint.08-26-2010
20100161155AUTOMATIC FLIGHT CONTROL HELICOPTER - The invention relates to an autonomous helicopter for recreational purposes or for a swarm-type surveillance system, characterised in that the helicopter has a complete automatic flight control, and in that the flight thereof is stable and automatic due to a device for the automatic control of the altitude, comprising at least two optical receivers, at least one optical emitter, at least two channels for processing signals of the receivers, and at least two motors controlling at least two propellers, at a speed proportional to the total amount of signals received. Said helicopter avoids obstacles by means of an orientation device controlled by the difference between the signals of the two receivers. It advances at a regular speed by means of a shift of the centre of gravity thereof in front of the axis of the two lifting propellers.06-24-2010
20100152927METHOD AND DEVICE FOR OPTIMIZING THE FLIGHT OF AN AIRCRAFT - The invention relates to a method for optimizing the flight of an aircraft comprising a flight management system, the said flight management system using a first cost index (CI06-17-2010
20100217458INTERACTIVE INFORMATION SYSTEM FOR AN AIRPLANE - An interactive information system is indicated for an aircraft to provide passengers with information, which access both an onboard data storage device and an off-board data storage device. A computer uses the onboard and off-board data to compute informative data, which are then visualized to the passenger. The passenger can interactively determine the form and type of data generation and preparation at any time.08-26-2010
20090076668Method and apparatus for providing power in an aircraft to one or more aircraft systems - A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear.03-19-2009
20100241291Autotiller control system for aircraft utilizing camera sensing - An automatic control system for directional control of an aircraft moving on the ground utilizing computer vision methods and camera sensing methods (visible, infrared or microwave) to optically recognize and track taxiway navigation features thereby providing pilot television picture steering cues or force inputs to the nosewheel steering system to maintain the aircraft on the centerline.09-23-2010
20100222942TAXI BRAKE INHIBIT SYSTEM - A taxi brake inhibit system overcomes problems of discontinuities in pedal “feel” that can occur by use of a taxi brake inhibit system, by adding a new pedal “feel” logic in which twice the brake force is commanded for a given brake pedal application when taxi brake inhibit is active. The taxi brake inhibit system relies upon two different brake force vs. brake pedal application curves to compensate for the difference in deceleration that is achieved for a given brake pedal application depending upon whether the taxi brake inhibit is active or inactive. Such system effectively eliminates undesirable deceleration bumps, yaw effects and changes in pedal feel during braking. The taxi brake inhibit feature is also shut off to both fore-aft brake pairs if any non-normal taxi brake inhibit condition exists on either fore-aft brake pair.09-02-2010
20100211236WIRELESS ENGINE MONITORING SYSTEM - A wireless engine monitoring system (WEMS) includes an engine monitoring module that is mounted directly on an aircraft engine and records, stores, encrypts and transmits full flight engine data. The system preferably interfaces to the Full Authority Digital Engine Controller/Engine Control Unit (FADEC/ECU) and can record hundreds of engine parameters with a preferred sampling frequency of about one second. The engine monitoring module is preferably formed as a miniaturized module directly mounted on the aircraft engine within its cowling and has a conformal antenna. The engine monitoring module can also upload data for onboard processing.08-19-2010
20130218372Weapons Stores Processor Panel For Aircraft - An aircraft weapons control system including a weapons stores processor panel for receiving input signals from a weapons input; a weapons interface for receiving fire signals from the weapons stores processor panel to control firing of aircraft weapons; and a flight management system in communication with the weapons stores processor panel and the weapons interface, the flight management system providing control signals to the weapons interface; wherein the weapons stores processor panel implements safety interlocks to prevent or enable firing of the aircraft weapons08-22-2013
20090319099COMPUTER MAINTENANCE SYSTEM FOR AN AIRCRAFT WITH REMOTE TERMINAL - The present invention relates to a computer maintenance system for an aircraft comprising a server hosting maintenance software and at least one access terminal. The system comprises a KVM switch over IP linked to said server. The terminal is adapted to connect to said switch by means of a TCP/IP connection and hosts a client application. Symmetrically, the switch hosts a server application, said applications being suitable for implementing a protocol for remotely accessing a video frame buffer. Each video frame is transmitted from the server application to the client application in the form of bitmap image data, uncompressed or else compressed by a lossless compression algorithm.12-24-2009
20090319097HAND CONTROLLER ASSEMBLY - A user input device for a vehicular electrical system is provided. The user input device includes a handle sized and shaped to be gripped by a human hand and a gimbal assembly within the handle. The gimbal assembly includes a first gimbal component, a second gimbal component coupled to the first gimbal component such that the second gimbal component is rotatable relative to the first gimbal component about a first axis, and a third gimbal component coupled to the second gimbal component such that the third gimbal component is rotatable relative to the second gimbal component about a second axis.12-24-2009
20090112379Method and Arrangement for Providing a Fault Diagnosis For At Least One System - The present invention provides a method for providing a fault diagnosis for at least one system, in particular of an aircraft. The method comprises: (a) providing a number N04-30-2009
20080294305ROTORCRAFT CONTROL SYSTEM11-27-2008
20090112377System and Method for Virtual Information - A system for providing information to at least one passenger onboard a mobile platform (such as a train, marine vessel, aircraft or automobile) is provided. The system includes a display device that displays the information. The system also includes a source of user input coupled to the display device that enables the at least one passenger to request the information. The information includes at least galley information. The system further includes a galley control module that generates galley data that includes at least one food service item available onboard the mobile platform, and a graphical user interface module that displays the at least one food service item available onboard the mobile platform to enable the at least one passenger to select at least one of the at least one food service item.04-30-2009
20090112378System and Method for Aircraft Interior Annunciator - A system for an interior annunciator onboard a mobile platform (such as a train, marine vessel, aircraft or automobile) is provided. The system includes at least one speaker onboard the mobile platform. The system also includes a flight management control module that generates flight management data that indicates at least one status of an operation of the mobile platform. The system further includes an auditory control module that generates nonverbal auditory data based on the at least one status of the operation of the mobile platform. The nonverbal auditory data is broadcast by the at least one speaker to communicate the at least one status of the operation of the mobile platform to at least one passenger onboard the mobile platform.04-30-2009
20110112705ELECTRONIC CONTROL DEVICE FOR A PILOTING MEMBER WITH MULTIFUNCTIONAL MICROCONTROLLERS, PILOTING DEVICE AND AIRCRAFT - An electronic control device for an aircraft piloting member mounted on an electromechanical supporting box (05-12-2011
20080319590Systems for announcing the health of ball screw actuators and ball recirculation - A method of determining variations in operating characteristics of a mechanical system having a rotatory mode of operation and bearing balls entrained within a bearing balls recirculation system. There are provided the steps of first monitoring operating impulses generated by the mechanical system during a first interval of operation; first analyzing the operating impulses obtained during the first interval to determine the intensity and frequency of the operating impulses; first correlating the operating impulses obtained during the first interval to corresponding angular positions of the rotatory mode of operation; and first producing a first record of the intensity and frequency of the operating impulses obtained during the first interval correlated to the corresponding angular positions of the mechanical system. The health of bearing balls within the recirculation system is determined by monitoring the vibration characteristic of the recirculation system, which is correlatable to the specific bearing balls.12-25-2008
20130131896METHOD OF ASSISTED PILOTING OF A ROTARY WING AIRCRAFT HAVING AT LEAST ONE PROPULSION PROPELLER, AN ASSISTED PILOTING DEVICE, AND AN AIRCRAFT05-23-2013
20090069958SYSTEME DE FREINAGE DIFFERENTIEL - A braking system for the landing gear of an aircraft, which landing gear includes a bogey containing at least four wheels, each equipped with a brake, with the bogey having at least two axles that are connected to the aircraft by a telescoping strut, wherein when the aircraft makes a low-speed turn around a center of rotation, the straight line linking the center of rotation of the turn to the barycenter of the landing gear does not pass between the front wheels and the rear wheels of the landing gear which system further includes means for applying differential braking between the front wheels and the rear wheels of the landing gear.03-12-2009
20090037035AIRCRAFT GAS TURBINE ENGINE BLADE TIP CLEARANCE CONTROL - A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.02-05-2009
20090037034VEHICLE PERFORMANCE MONITORING SYSTEM WITH MULTI-LEVEL CACHING - A system and method for monitoring vehicle performance including multi-level caching. The system includes a vehicle portion with sensors, a vehicle caching data server, and a wireless transceiver and a monitoring station portion with monitoring workstations, a monitoring caching data server, and a wireless transceiver. The monitoring caching data server receives and aggregates requests for vehicle performance data from the monitoring workstations based on request priority and available bandwidth. The vehicle caching data server stores vehicle performance data from the sensors and selectively transmits a subset of the vehicle performance data to the monitoring caching data server in response to aggregate requests.02-05-2009
20130138269MULTI CORE VEHICLE MANAGEMENT COUNTERMEASURES SYSTEM AND METHOD - A computerized method for performing countermeasure transmission of decoy vehicle data. The method can include receiving a vehicle management data message from one of a plurality of vehicle management system components. The vehicle management data message can have data indicating at least one destination component, and the at least one destination component can include a civil transponder. The method can include transforming said vehicle management data message into a decoy vehicle management data message and transmitting the decoy flight management data message to at least one of the at least one destination component(s).05-30-2013
20130138270FLIGHT CONTROL LAWS FOR AUTOMATIC HOVER HOLD - A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope; engaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; and engaging a position hold with a control law position hold architecture as the aircraft enters the second flight envelope.05-30-2013
20130138271DISTRIBUTED AVIONICS - A distributed avionics system arranged in an aerial vehicle for controlling at least one avionics function. A plurality of avionics processing subsystems are interconnected in a network. Each avionics processing subsystem includes a processor arranged to process at least one task so as to provide a set of data messages including at least one unit of data related to controlling the at least one avionics function on basis of provided input data, related to conditions of the at least one avionics function. A memory module is in operative connection with the processor and is arranged to store instructions for the processor to process the at least one task. At least one of the avionics processing subsystems is arranged to transmit at least one synchronization cycle start signal onto the network05-30-2013
20110004361METHOD AND DEVICE FOR ESTIMATING THE FORCES EXERTED ON A CONTROL SURFACE OF AN AIRCRAFT - The device (01-06-2011
20100332054AUTOMATED DECISION AID TOOL FOR PROMPTING A PILOT TO REQUEST A FLIGHT LEVEL CHANGE - Provided are methods and systems for the automatic calculation and presentation of data on a display device alerting a pilot that a change in flight plan is desirable, possible and administratively compliant under air traffic control protocol. The methods and systems may automatically request the flight clearance over a data link or the pilot may override the data link.12-30-2010
20100332055ASSISTANCE PROCESS AND DEVICE FOR MANAGING AN IN-FLIGHT REFUELING - An assisting process and device for managing an in-flight refueling is disclosed. The device (12-30-2010
20100332052FAULT TOLERANT FLIGHT CONTROL SYSTEM - A method, apparatus, and computer program product for identifying a number of air states for a vehicle. A deflection of a control surface associated with an actuator is identified to form an identified deflection. A current in the actuator is identified to form a measured current. The number of air states for the vehicle is estimated using the identified deflection and the measured current.12-30-2010
20110029159METHOD AND DEVICE FOR REDUCING ON AN AIRCRAFT LATERAL EFFECTS OF A TURBULENCE - A method and device for reducing on an aircraft lateral effects of a turbulence. The device (02-03-2011
20110029158METHOD AND SYSTEM FOR VERTICAL NAVIGATION USING TIME-OF-ARRIVAL CONTROL - A method and systems for controlling a speed of a vehicle are provided. The control system includes an input device configured to receive a required time of arrival (RTA) at a waypoint and a processor communicatively coupled to said input device, said processor programmed to automatically determine a dynamically adjustable range for an autothrottle control using an RTA error and a speed control tolerance, the RTA error representing a difference between an estimated time of arrival (ETA) and the RTA, the speed control tolerance representing a tolerance range about the vehicle speed profile. The control system also includes an output device communicatively coupled to said processor, said output device is configured to transmit at least one of a thrust control signal and a drag control signal to a speed control system of the vehicle.02-03-2011
20110040428TRANSPORTATION INFORMATION MANAGEMENT SYSTEM - A computer-implemented transportation information management system and method permits entry, recording, and transmission of operation and maintenance data related to FAA recordkeeping and recording requirements within an SQL database. A secure website permits entry and display of operation and maintenance data as well as facilitating data input using input devices such as a cellular telephone, a personal digital assistant, a personal computer, and a portable computer. The system outputs aircraft operation and maintenance data, automatic alerts of pilot flight and duty time limitations, and flight tracking and monitoring information via a spreadsheet, electronic mail message, text message, and a completed FAA mandatory reporting requirement forms to the aforementioned data input devices. Operation and maintenance data is automatically and continuously transferred to the FAA to populate FAA flight tracking data systems and air traffic control data system.02-17-2011
20110040430INTEGRITY MONITORING OF INERTIAL REFERENCE UNIT - Systems, methods, and machine-executable programming products adapted for the control of aircraft or other vehicles by receiving from at least one Inertial Reference System (IRS), including a plurality of Inertial Reference Units (IRUs), signals representing vehicle state data; receiving from at least one Augmented Direct Mode Sensor (ADMS) signals representing independently-acquired vehicle state data corresponding to at least a subset of the signals received from the IRS; performing signal selection and fault detection processes on the signals received from the at least one IRS and on the corresponding signals received from the ADMS; based at least partly on the signal and fault detection processes, determining whether at least one component of at least one of the IRS and ADMS is in a fault condition; and based on the fault condition, providing to at least one vehicle control system device one or more vehicle control command signals.02-17-2011
20110046818ONBOARD AIRPLANE COMMUNITY NOISE AND EMISSIONS MONITOR - A method for monitoring airplane noise and emissions may include receiving a predetermined set of engine performance data for an airplane and receiving a predetermined set of airplane flight data for the airplane. The method may also include predicting at least one of a noise level and an emissions level from the airplane at each of a plurality of ground based noise and emissions monitoring stations based on the predetermined set of engine performance data and the predetermined set of airplane flight data. Each of the plurality of ground based noise and emissions monitoring stations is located at a predetermined geographic location along an expected flight path of the airplane. The method may also include presenting at least one of the predicted noise level and the predicted emissions level on a display to a pilot of the airplane to permit operation of the airplane to substantially minimize at least one of an actual noise level and an actual emissions level at each of the plurality of ground based noise and emissions monitoring stations.02-24-2011
20110046817Incremental Position-Based Guidance For A UAV - Disclosed herein is a method and system for flying a ducted-fan aerial vehicle, such as an unmanned aerial vehicle (UAV). The method includes receiving a flight plan comprising a plurality of waypoints and a plurality of path segments connecting the plurality of waypoints in an order of execution. The method further includes determining actual flight instructions for the ducted fan unmanned aerial vehicle based on (i) the received flight plan, (ii) a predetermined set of operating parameters associated with the ducted fan unmanned aerial vehicle, and (iii) an iterative analysis of a plurality of ordered triples. The method further includes sending the actual flight instructions to at least one processor of the ducted fan unmanned aerial vehicle configured to implement one or more portions of the actual flight instructions.02-24-2011
20110046822Method for Reducing Outside Air Inflow Required for Aircraft Cabin Air Quality - A method for calculating an aircraft fuselage leakage calculation of an aircraft is provided. The method comprises determining a calculation period for an aircraft fuselage leakage value and inputting the calculation period into a computer to obtain a first input data. The method further comprises obtaining one or more outside air inflow rates and inputting the one or more outside air inflow rates into the computer to obtain a second input data. The method further comprises obtaining one or more air outflow rates and inputting the one or more air outflow rates into the computer to obtain a third input data. The method further comprises accumulating the first input data, the second input data, and the third input data in the computer to obtain an accumulated input data. The method further comprises processing the accumulated input data with a process software to obtain an output data in the form of a calculated aircraft fuselage leakage value. The method further comprises sending the output data to a data file. The method further comprises using the calculated aircraft fuselage leakage value to calculate an aircraft fuel savings potential value.02-24-2011
20110046819METHOD AND SYSTEM FOR DEACTIVATING A STEERING SYSTEM OF AN AIRCRAFT'S FRONT LANDING GEAR - A method for deactivating a steering system of a front landing gear of an aircraft, including detecting an activated status of the steering system, detecting a pilot control unit in neutral position, detecting towing conditions of the aircraft, detecting a rotational movement of the nose gear, and deactivating the steering system when operations to are verified. The disclosed embodiments also concern a system for implementing this method.02-24-2011
20110046820TEST EQUIPMENT FOR TESTING AN ADDITIONAL CENTER TANK (ACT) SYSTEM OF AN AIRCRAFT - The present invention provides test equipment for testing an additional center tank (ACT) system of an aircraft. The ACT system comprising control means configured to perform functions of an Auxiliary Fuel Management Computer (AFMC) and an Auxiliary Level Sensing Control Unit (ALSCU). The test equipment comprises at least one test module adapted for coupling to the ACT system in place of at least a portion of the control means, the test module comprising means for generating one or more test signals and outputting the test signals to the ACT system.02-24-2011
20110245999AIRCRAFT HEALTH MONITORING AND DESIGN FOR CONDITION - A system and method for automatically varying the flight envelope of an aircraft based upon the material health of the aircraft and the flight environment is provided. The system includes a plurality of structural health monitoring and load sensors that determine the approximate size and the approximate location of the damage. The system performs residual strength calculations for individual aircraft components to determine the overall aircraft residual strength. The system uses these calculations to determine a maximum flight envelope based on the overall aircraft residual strength, and transmits this information to the flight controller and optionally to the pilot.10-06-2011
20090069957UNMANNED HELICOPTER - GPS devices (GPS receivers and corresponding GPS antennas) for detecting a location of an airframe are provided. An autonomous control section (e.g., an autonomous control box) including a data communication device for communicating with the ground and a control board having a built-in control program is provided. An unmanned helicopter flies depending on airframe data such as an attitude and a speed of the airframe, engine speed, and a throttle angle and flight data such as a location and a direction of the airframe. The autonomous control section is provided with a plurality of different type of GPS devices.03-12-2009
20100241292PREDICTED PATH SELECTION SYSTEM AND METHOD FOR HAZARD CODING IN SELECTIVELY CONSTRAINED AIRCRAFT CONTROL SYSTEMS - A surveillance system detects potential hazards and alerts the pilot to them. The alerts can be modified to indicate proximity to the predicted path of the aircraft. An autopilot receives instructions from a flight management system (FMS) regarding a planned path and is subject to constraints preempting the planned path. The surveillance system selects which of the planned and a constrained path will be followed for alerting and hazard coding purposes. Means are disclosed to determine when the constrained path will be followed by evaluating the current position of an aircraft, the planned path, and the constraint data.09-23-2010
20110125346PROTECTION ENVELOPE SWITCHING - An apparatus defines a protection envelope in an aircraft, including a processor and at least one sensor, each sensor being coupled with the processor, the processor executing at least one neural network based algorithm. The at least one sensor monitors flight parameters of the aircraft thereby generating monitored flight parameters. The processor divides the performance envelope of the aircraft into predefined flight regimes, wherein for each predefined flight regime, the processor defines and stores a suitable protection envelope. The processor determines an estimated flight regime of the aircraft using the neural network based algorithm based on the monitored flight parameters. The processor selects a respective suitable protection envelope for the aircraft based on the estimated flight regime.05-26-2011
20090048722COMPOUND AIRCRAFT CONTROL SYSTEM AND METHOD - The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of operational objectives each of which is designed to achieve any particular command.02-19-2009
20100131123INPUT/STEERING MECHANISMS AND AIRCRAFT CONTROL SYSTEMS - Input/steering mechanisms and aircraft control systems are provided. In an embodiment, by way of example only, an input/steering mechanism is provided for use with an aircraft control system. The input/steering mechanism includes a handlebar, a first panel extending from the handlebar, and a first portion of an alphanumeric keyboard disposed on the panel and adapted to receive a manual input from a user and to transmit an output signal to the aircraft control system in response to the manual input.05-27-2010
20090216391INERTIAL SIGNALS FOR FLIGHT CONTROL BACKUP MODE - A flight control system is provided that includes a reference system and flight control actuators. The reference system includes one or more sets of gyroscopes and accelerometers. At least one set of the gyroscopes and accelerometers are configured to provide a first output of a first set inertial signals for normal mode flight control and second output of a second different set of inertial signals for backup mode flight control. The flight control actuators are configured to be controlled by one of the first set of inertial signals and the second set of inertial signals.08-27-2009
20110178658SYSTEMS AND METHODS FOR MONOCULAR AIRBORNE OBJECT DETECTION - Systems and methods for airborne object detection using monocular sensors are provided. In one embodiment, a system for detecting moving objects from a mobile vehicle comprises: an imaging camera; a navigation unit including at least an inertial measurement unit; and a computer system coupled to the image camera and the navigation unit. The computer system executes an airborne object detection process algorithm, and calculates a transformation between two or more image frames captured by the imaging camera using navigation information associated with each of the two or more image frames to generate a motion compensated background image sequence. The computer system detects moving objects from the motion compensated background image sequence.07-21-2011
20100070111SYSTEM FOR AERIAL DELIVERY OF FIRE RETARDANT - A system for launching, controlling and delivering in a preselected target pattern a plurality of low-cost, guided fire-retardant-containing vehicles, i.e., “smart water bombs” equipped with control surfaces sufficient to provide limited lift and maneuverability to respond to guidance command to place it at a selected GPS coordinate within a large footprint in time and space and to discharge its payload of fire retardant at a preselectable altitude in a very precise manner and dispersion pattern. A controller determines bombing patterns and timing for all bombs and trajectories for each guided bomb. Dynamic differential equations are used to determine location and time of release of the guided bombs to achieve the target while avoiding collisions among guided bombs and aircraft.03-18-2010
20100070109SYSTEM AND METHOD FOR DISPLAYING A DIGITAL TERRAIN - Methods and systems for displaying a digital terrain to a user of a vehicle are provided. First, second, and third actual terrain data points are received. The third actual terrain data point is between the first and second actual terrain data points. If the third actual terrain data point is above a line interconnecting the first and second actual terrain data points, the first actual terrain data point is modified such that the third actual terrain data point is not above a line interconnecting said modified first actual terrain data point and the second actual terrain data point. A digital terrain is displayed to the user of the vehicle. The digital terrain includes a first digital terrain data point corresponding to the modified first actual terrain data point.03-18-2010
20100070110METHODS AND SYSTEMS FOR INDICATING FUEL REQUIRED TO REACH A LOCATION - Methods and systems are provided for indicating on a display device whether a vehicle has sufficient fuel remaining to travel from a first location to a second location. An exemplary method involves determining the amount of fuel required for the vehicle to travel from the first location to the second location. If the amount of fuel required is greater than a threshold fuel value associated with the first location, the method displays a graphical representation of the second location on the display device using a first visually distinguishable characteristic. If the first amount of fuel is less than the threshold fuel value, the method displays the graphical representation of the second location on the display device using a second visually distinguishable characteristic.03-18-2010
20100070112PROGRESSIVE TAKEOFF THRUST RAMP FOR AN AIRCRAFT - A method is presented for controlling thrust generated by aircraft engines. Engine thrust is controlled based on aircraft groundspeed and airspeed during the initial part of takeoff. Limiting thrust at low groundspeed during the initial phase of takeoff has significant benefits that reduce engine stress during this brief but critical phase leading to flight. Logical elements combine both groundspeed and airspeed in such a way that the operator perceives a smooth progressive thrust increase consistent with normal engine operation.03-18-2010
20110071708ASSISTED PILOTING METHOD AND DEVICE FOR AN AIRCRAFT FOR USE IN THE EVENT OF A FIRST LIMIT INDICATOR BREAKING DOWN - An assisted piloting method for an aircraft having at least two engines (03-24-2011
20110071705Aircraft Power Management - An electric power management system of a vehicle may interconnect a power plant, a propeller drive unit, and a battery via a bus. A controller may direct the operation of the power plant and the propeller drive unit. In a slow control mode, the propeller drive unit may react slowly to small throttle change requests. In the slow control mode, the propeller drive unit may draw power completely or substantially from the power plant. Upon a throttle request to rapidly change propeller drive unit speed more than a threshold amount, the controller may direct that the propeller drive unit quickly obtain the requested speed by drawing power required from the battery in excess of that being generated from the power plant. Subsequently, the controller may direct that the power plant increase power generation to maintain the propeller drive unit at the new speed, and recharge or float the battery.03-24-2011
20110071709HIGHLY REPRESENTATIVE REAL-TIME SIMULATION OF AN AVIONICS SYSTEM - Optionally-mixed highly representative real time simulation of at least part of an avionics system (03-24-2011
20110071707Method for Managing Power Boost in a Fuel Cell Powered Aerial Vehicle - An aerial vehicle is configured to operate in a base fuel cell operating mode and a fuel cell boost operating mode. A method for controlling the aerial includes providing a base fuel cell upper power limit. The method further includes controlling the fuel cell power level below the base fuel cell upper power limit when the aerial vehicle is operating in the base fuel cell operating mode. The method further includes operating the fuel cell above the base upper fuel cell power limit when the aerial vehicle is operating in the fuel cell boost operating mode.03-24-2011
20090018713SYSTEM FOR AIDING THE TAXIING OF AN AIRCRAFT - The invention relates to an integrated system carried onboard the aircraft used during taxiing or air/ground and ground/air transitions whose final objective is assistance to the crew in collaboration with the ground control authority. The system groups together a set of devices for mapping 01-15-2009
20120303183NETWORK, IN PARTICULAR FOR AN AIRCRAFT AND SPACECRAFT, METHOD AND AIRCRAFT AND SPACECRAFT - The present invention provides a network, in particular for an aircraft and spacecraft, comprising a network line and at least two network access devices which are interconnected by the network line and between which data of different levels of priority can be transmitted, the network access devices being formed so as allocate data with a level of priority allocated to the respective data, at least two different levels of priority being provided for the data depending on the relevance of the respective data, and the data being transmitted on the network line in fixed time slots depending on the level of priority assigned in each case. The present invention further provides a method and an aircraft and spacecraft.11-29-2012
20110060482CONTROL ASSEMBLY - A control assembly operable in the event of overheating of an engine electronic controller on an aircraft. The assembly including one or more temperature sensors located in the vicinity of the aircraft engine and connected to a control unit. The control unit is arranged to measure the temperature or temperatures detected by the sensors, and to determine whether in view of detected increased temperatures, a situation constitutes an emergency situation or a controlled situation. The control unit communicates a controlled situation to a pilot of the aircraft, and automatically causes an override action to occur to the aircraft engine when an emergency situation is determined.03-10-2011
20110251739DISTRIBUTED FLY-BY-WIRE SYSTEM - A system includes a plurality of fly-by-wire control units to control flight control surfaces of an airplane, wherein each control unit is adapted to operate independently of other control units and directly control an actuator to control a control surface as a function of direct pilot control device input.10-13-2011
20100305781PREDICTING AIRCRAFT TRAJECTORY - The present invention provides a computer-implemented method of producing a description of aircraft intent expressed using a formal language. The description may be used to predict aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to generate a set of instructions describing both the aerodynamic configuration of the aircraft and the motion of the aircraft. These instructions are checked to ensure that they describe unambiguously the aircraft's trajectory. The instructions are then expressed using a formal language.12-02-2010
20100114408MICRO AERIAL VEHICLE QUALITY OF SERVICE MANAGER - The present invention provides methods and systems for adjusting video quality outputted by an aerial vehicle to manage the data stream bandwidth to match the needs of each mission segment. A mission segment is monitored in order to determine a preferred video quality of service. A quality of service is set based on the monitored mission segment. The quality of service is selectively altered based on a change of at least one of a mission segment or an environmental condition.05-06-2010
20100262318Electronic flight bag user interface system - An electronic flight bag user interface system that has a multi-function flight information display unit in electronic communication with a remote processing unit. The processing unit is in electronic communication with an aircraft avionics system. Pre-loaded flight information allows the user to access and display flight information on the display unit in digital electronic format, including charts and plates, flight manuals, weather information, camera viewing information, ship library information, and revision status of software programmed in the processing unit and revision status of pre-loaded charts, plates and manuals. The system operates on a single or a dual operating system platform, a Windows® based operating system and the other based on a DO178B certified operating system.10-14-2010
20120123615METHOD AND A SYSTEM FOR ESTIMATING A TRAJECTORY OF A MOVING BODY - A hybrid simulation method uses a simulator tool feeding kinematics commands to a movement simulator on which a moving body is mounted and to a target representative of an objective to be reached by the moving body, and on detection of an event representative of overshooting or changing a first designated objective for this moving body, the method includes a positioning stage associated with a second designated objective for the moving body, including comparing positions executed by the movement simulator in response to transition kinematics commands with a first predetermined setpoint position and activating a first marker if a position substantially the same as the first setpoint position is detected; comparing positions executed by the target in response to transition kinematics commands with a second predetermined setpoint position and activating a second marker if a position substantially the same as the second setpoint position is detected; when the first and second markers are activated, a step of evaluating a difference between the current kinematics command supplied to the movement simulator and the target by the digital simulator tool; and, if this difference is below a particular threshold, a piloting stage including applying corrective terms linked to the setpoint positions to the kinematics commands coming from the simulator tool before they are fed to the movement simulator and to the target.05-17-2012
20120203401Onboard Maintenance System Network Optimization - An aircraft communication system includes an aircraft component, an Integrated Modular Avionics (IMA) unit, an Onboard Maintenance System (OMS), and a switch. The switch routes data provided by the aircraft component via a first communications protocol to the IMA unit, and mirrors the routed data to the OMS via a second communications protocol. The OMS processes and stores the received data, part of the received data, or the results of said processing.08-09-2012
20100004799Systems and Methods for Alleviating Aircraft Loads with Plasma Actuators - Systems and methods for alleviating aircraft loads with plasma actuators are disclosed. A method for operating an aircraft in accordance with a particular embodiment includes receiving an input corresponding to an aircraft component structural response to an aerodynamic load. The method can further include, based at least in part on the input corresponding to the aircraft component's structural response, reducing the structural response to the aerodynamic load by activating at least one plasma actuator carried by the aircraft, in accordance with one or more activation parameters.01-07-2010
20080243313GOVERNOR FOR A ROTOR WITH A VARIABLE MAXIMUM COLLECTIVE PITCH - A governor configured to regulate the rotational velocity of one or more rotors of an aircraft by adjusting a collective blade pitch of the one or more rotors. In one embodiment, the governor comprises a control monitor, a maximum pitch module, a rotor module, and a pitch adjustment module. The control monitor is configured to monitor one or more flight control inputs that are controllable by an operator of the aircraft. The maximum pitch module is configured to dynamically determine a maximum collective blade pitch based on the one or more flight control inputs monitored by the control monitor. The rotor module is configured to monitor information related to the rotational velocity of the one or more rotors. The pitch adjustment module is configured to (i) receive information related to the rotational velocity of the one or more rotors from the rotor module and (ii) adjust the collective blade pitch of the one or more rotors to regulate the rotational velocity of the one or more rotors.10-02-2008
20110213513METHOD FOR AUTOMATIC AVOIDANCE OF COLLISIONS BETWEEN A CRAFT AND FURTHER OBJECTS - A method for controlling the motion of an object for the avoidance of collisions with obstacles includes: detecting of at least one non-stationary or stationary obstacle; defining a safety zone around the obstacle which moves together with the obstacle; detecting whether the obstacle, including its safety zone, is in a collision course with the object; calculating an avoidance trajectory, which by-passes the obstacle, such that the avoidance trajectory, at least approximately, is circularly shaped and that the circularly-shaped avoidance trajectory, or a straight line tangentially linked thereto, is tangent to the safety zone around the obstacle; and driving the object such that it follows, at least approximately, the calculated avoidance trajectory, whereby the calculated avoidance trajectory is tangentially linked to the previous trajectory.09-01-2011
20090118875Systems and methods for coordination of entities and/or communicating location information - Systems and methods that may be employed to communicate location information between two or more aerial vehicles or other types of vehicles or other entities, and/or that may be used to facilitate coordinated operations of two or more such entities. In one example, an aerial vehicle may be kept aware of one or more location (e.g., longitude, latitude, etc.) and/or flight characteristics (e.g., altitude, directional heading, airspeed, attitude, etc.) of one or more other adjacent aerial vehicles, and each such aerial vehicle may use that location information to adjust its flight path to maintain a safe sphere of empty airspace around itself.05-07-2009
20090005917System and method of carbon monoxide and fire detection and protection - A carbon monoxide and fire detection system and method are provided for vehicles, particularly light aircraft, which includes CO and smoke/heat detectors located in or near the pilot cabin that, in the event unsafe levels of CO is detected in the cabin or a fire is detected in the engine compartment, an electronic signal from the respective detector causes the heated ram-air and fresh-air control box valves to open or close to restrict heated air contaminated with CO and allow fresh-air into the cabin in the case of CO detection, or closing both valves thereby restricting a fire from entering the cabin through the heated ram-air or fresh air vents, as the case may be.01-01-2009
20100305782AIRBORNE RIGHT OF WAY AUTONOMOUS IMAGER - An automated airborne video recording system for imaging pipeline or electric line rights-of-way, irrigation canals, or any other linear ground features. The system includes a gimbaled, stabilized camera system, a data recorder, and autonomous imager software that computes the shortest vector between the aircraft position and the pipeline based on the aircraft GPS and the Geographic Information Database. The system then commands the stabilized camera system to point directly at the pipeline regardless of the aircraft position and orientation, automatically collecting continuous NTSC or digital video of the entire right of way.12-02-2010
20100324754Samara wing - A samara wing including a main wing with a leading edge and a trailing edge. An aileron has a leading edge and a trailing edge and is pivotally attached proximate the trailing edge of the main wing and separated therefrom by a gap. The aileron is rotatable between the first position where the trailing edge of the aileron is facing forward in a plummet mode of operation and a second position where the trailing edge of the aileron is facing rearward typically for an autorotation mode of operation.12-23-2010
20080255713Dynamic Adjustment of Wing Surfaces for Variable Camber - The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.10-16-2008
20110054718DYNAMIC WEATHER SELECTION - The different advantageous embodiments provide a system comprising a weather band selection process and a processor unit. The processor unit is configured to run the weather band selection process. The weather band selection process identifies a flight trajectory associated with an aircraft, identifies weather information for the flight trajectory, and identifies a weather band selection for the aircraft using the flight trajectory, aircraft information and the weather information.03-03-2011
20110022249Distributed Architecture for All Radionavigation Aids - The present invention relates to a distributed architecture for all aerial navigation aids. So that this architecture makes it possible to reduce the weight and/or the bulk of the cables linking the antennas to the corresponding equipment, as well as the weight and/or the bulk of at least part of said equipment, a part at least of the receivers is sited remotely in proximity to the corresponding antennas, and a part at least of the power supply for the equipment of the aircraft is centralized, and this centralized supply distributes a stabilized DC power supply to the remotely sited equipment.01-27-2011
20110060483DEVICE FOR AIDING THE NAVIGATION AND GUIDANCE OF AN AIRCRAFT, AND SYSTEM COMPRISING SUCH A DEVICE - Device for aiding the navigation and guidance of an aircraft, and system comprising such a device. The device (03-10-2011
20110264307GNSS OPTIMIZED AIRCRAFT CONTROL SYSTEM AND METHOD - A GNSS system in combination with a hydraulically-actuated, airborne dispenser for a dry material crop dusting system to optimize the distribution of dry materials over a particular tract of land. A GNSS subsystem is included using at least one GNSS antenna and one GNSS receiver located on the aircraft. The aircraft is equipped with an electronic/hydraulic crop dusting subsystem connected to a GNSS CPU. The GNSS ranging signals received by the antennas are processed by a receiver and processor system for determining the vehicle's position and dynamic attitude in three dimensions (3D). A graphical user interface (GUI) placed in the vehicle will give the driver a real-time view of his or her current bearing as well as a calculated “optimal path” based on calculations and variable data, such as wind speed and direction, material moisture content, altitude, air speed and other conditions. The system is adapted for operation in a differential GNSS (DGNSS) mode utilizing a base station at a fixed location.10-27-2011
20110071706METHOD FOR MANAGING POWER AND ENERGY IN A FUEL CELL POWERED AERIAL VEHICLE BASED ON SECONDARY OPERATION PRIORITY - A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further includes determining priority levels of secondary operations and providing power for secondary operations based on the priority levels.03-24-2011
20100292869AIRCRAFT DISPATCH INFORMATION - Systems and methods to manage aircraft dispatch information are provided. A particular method includes receiving fault information at a dispatch information computing system. The fault information is associated with an aircraft. The method also includes accessing operational restriction information associated with the aircraft based on the fault information. The method further includes automatically determining a set of bottom line operational limitations of the aircraft based on the fault information and the operational restriction information. The method also includes generating customized checklists for the various users of the information. The method also includes sending output data from the dispatch information computing system to an output device. The output data identifies the set of bottom line operational limitations of the aircraft and tasks to be completed by the various users.11-18-2010
20100292870FADEC AND AVIONIC COMPONENT DISTRIBUTED ARCHITECTURE - The invention relates to a device for motorized aircraft comprising at least one avionic component (11-18-2010
20110118907MULTIPURPOSE MODULAR AIRSHIP SYSTEMS AND METHODS - Embodiments according to the methods and systems provide for the selection, assembly, deployment, exploitation of data collected, redeployment, retrieval and stowage of a remotely operated lighter than air (LTA) network of vehicles. From modular components stowed with a mobile platform, one or more LTA vehicles can be assembled, deployed and retrieved. Determining the desirable number of LTA vehicles and the modular components to be assembled for each vehicle can be performed through a computer recommending modular components based on mission parameters. A remote controller device can be used for pre-deployment setup, in-flight mission management and analysis of data gathered by a plurality of possible sensing devise operably attached to the one or more LTA vehicles.05-19-2011
20110118904METHOD AND SYSTEM TO REDUCE IMPACT OF NON-ATC DATALINK MESSAGES ON ATC DATALINK MESSAGES ON A SHARED AIR-GROUND COMMUNICATION LINK - A system to send air traffic control (ATC) data-link messages from an aircraft is provided. The system includes ATC applications in a first portion of an application layer, non-ATC applications in a second portion of the application layer; and a communication manager in the aircraft having two addresses for the aircraft. The communication manager includes a first copy of software in a first data link layer and a second copy of the software in a second data link layer. ATC data-link messages are sent from the aircraft independent of non-ATC data-link messages sent from the aircraft.05-19-2011
20110137492STABILIZED APPROACH TO A POINT IN DEGRADED VISUAL ENVIRONMENT - A flight control system includes a fly by wire system operable to provide predictive termination point symbology overlaid on a synthetic imagery displayed by a display system in response to a control system and a sensor system. A method to facilitate a VTOL aircraft approach to a terminal point includes integrating a flight director mode with a control system to provide a stabilized approach path to a termination point.06-09-2011
20110137494Systems and Methods for Velocity Profile Based Approach to Point Control - A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile based approach to point control module for an aircraft and a computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control are also provided.06-09-2011
20110137497AIRCRAFT PROVIDED WITH A DEVICE FOR ASSISTING THE PILOT WHEN CARRYING AN EXTERNAL LOAD WITH A SLING, AND A METHOD IMPLEMENTED BY SAID DEVICE - The present invention relates to an aircraft (06-09-2011
20110137495Method for Assisting in Rejoining a Vertical Descent Trajectory and Associated Device - A method is provided for assisting in rejoining a vertical descent trajectory that an aircraft is assumed to have to follow, using a flight management system FMS embedded onboard the aircraft, and includes the following steps: calculation of a vertical deviation VDEV, in the vertical plane, between the aircraft and the vertical descent trajectory, and comparison between the vertical deviation VDEV and a predetermined deviation threshold SVDEV; when the vertical deviation VDEV reaches the deviation threshold SVDEV, a step during which the activation of an optimized mode for catching up on the vertical descent trajectory is authorized; if the optimized mode for catching up on the vertical descent trajectory is activated, piloting of the aircraft by the flight management system FMS in optimized catch-up mode, that is to say at minimum thrust with a target rejoining speed in level VCRP and a target rejoining speed in downward trajectory, the target rejoining speed in level VCRP being equal to the maximum L/D ratio speed of the aircraft uprated by a first value V06-09-2011
20100324755Method and system for resolving traffic conflicts in take-off and landing - A method and system for resolving existing and potential traffic conflicts that may occur during take-off and landing in aviation that includes means of monitoring movements on the runway, its approaches and environs to determine whether a conflict or potential conflict exists, means to resolve a conflict and to generate an output pertaining to this resolution.12-23-2010
20100324756SYSTEMS AND METHODS FOR VALIDATING PREDETERMINED EVENTS IN RECONFIGURABLE CONTROL SYSTEMS - Systems and methods for validating predetermined events in reconfigurable control systems are provided. One method includes receiving, by a plurality of redundant processors operating in a first mode, a notice from two of three redundant sensors that the predetermined event occurred and reconfiguring the plurality of redundant processors to operate in a second mode in response to the notice. Another method includes receiving a first notice that one or more sensors detected that a first vehicle is coupled to a second vehicle at a primary control system and a secondary control system and reconfiguring the primary control system and the secondary control system to operate in another mode at substantially the same time in response to the notice.12-23-2010
20100185343METHOD OF CONTROLLING AN AIRCRAFT, THE METHOD IMPLEMENTING A VOTE SYSTEM - In the method of controlling an aircraft, a device implements the steps consisting in determining a first global value on the basis of only some amongst first individual values calculated by respective applications modifying at least one parameter to take account of how the determination step took place and determining a second global value on the basis of second individual values calculated by the respective applications and on the basis of the parameter(s).07-22-2010
20100179710METHOD AND DEVICE FOR MANAGING, PROCESSING AND MONITORING PARAMETERS USED ON BOARD AIRCRAFT - A standardized identification code is used to identify each flight parameter used on board an aircraft and to provide some of its characteristic information. Descriptive complementary information is advantageously associated with the identification codes to form parameter identification maps stored, for example, in a shared database. The parameter identification codes may in particular be used to perform certain checks when parameter values are received. These checks make it possible to process only the monitored parameter values and to generate alerts if an inconsistency is detected.07-15-2010
20110137493Method for Continuously and Adaptively Generating a Speed Setpoint for an Aircraft to Observe an RTA - Method for generating a flight speed profile of an aircraft (06-09-2011
20100082185System and Method for Calculating Flight Predictions by Vertical Sections - The invention relates to a system and a method for calculating flight predictions of an aircraft in which an intermediate prediction horizon is defined between the flight phase and the leg. This horizon, that is called vertical section, is defined such that the limit conditions that are applicable to it, for example the target speed, target altitude, characteristic altitude and maximum end-of-section distance, are valid for the entire vertical section. Thus, it is not necessary, in calculations to check the compatibility of the flight parameters with the applicable constraints, to arbitrarily select the constraint that must be given priority. Furthermore, this intermediate level architecture allows for a greater modularity of the prediction management software and therefore a greater factorization of the developments and greater ease of maintenance.04-01-2010
20110190963METHOD AND SYSTEM FOR AN OPTIMIZED UTILIZATION OF ENERGY RESOURCES OF AN ELECTRICAL SYSTEM - A method for optimized utilization of available energy resources/sources (08-04-2011
20110190966Control System For An Aircraft Propeller Drive - The invention relates to a control system for an aircraft propeller drive for controlling the power of a diesel engine (08-04-2011
20100030400AUTOMATIC SPEECH RECOGNITION SYSTEM AND METHOD FOR AIRCRAFT - A system and method which implement automatic speech recognition (ASR) and text-to-speech (TTS) programs to permit pilots, co-pilots, and other persons to more quickly and easily perform control and monitoring tasks on aircraft. The system may be used to automatically change the frequency of an aircraft radio when a pilot or co-pilot is instructed to do so by ATC.02-04-2010
20100030401FLIGHT DECK COMMUNICATION AND DISPLAY SYSTEM - A flight deck communication and display system (02-04-2010
20100023186FLY-BY-WIRE FLIGHT CONTROL SYSTEM WITH ELECTRONIC LEAD/LAG DAMPER ALGORITHM - An electronic lead/lag damper algorithm implemented as part of the fly-by-wire flight control system to minimize or eliminate mechanical lead/lag dampers of a rotary wing aircraft. The electronic lead/lag damper algorithm uses a cross-feed control methodology that band-pass filters pitch and roll rates and feeds back a signal to the lateral and longitudinal cyclic inputs to provide electronic stability to rotor lag modes.01-28-2010
20100017049Vehicle Health Management Systems and Methods - Systems and methods for managing the exchange of vehicle information between software modules with different safety importance. In one embodiment, a vehicle health management system includes a mission critical software module, a flight critical software module and a gatekeeper. The mission critical software module receives vehicle state information and provides it to the flight critical software module if the gatekeeper confirms the validity of the vehicle information.01-21-2010
20100017048MODEL BASED SENSOR SYSTEM FOR LOADS AWARE CONTROL LAWS - A flight control system includes a model-based sensor system which estimates angular accelerations to control rotor system moment such that loads on the aircraft structure are reduced to thereby allow an aircraft structural envelope to more closely follow an aircraft service flight envelope.01-21-2010
20100017047Systems and methods for remote display of an enhanced image - A system for providing remote display of an enhanced image comprises at least one image source and a processing element. The processing element is capable of receiving data from the image source, creating an enhanced image with the received data, and transmitting the enhanced image via a wireless link to a display device capable of displaying the enhanced image. The processing element may create the enhanced image by stitching image data from at least two image sources having different fields of view, fusing image data from at least two image sources having different image modalities, or combining image data from at least one image source with synthetic image data. The processing element may be further capable of modifying at least one transmission characteristic based on a bandwidth of the wireless link. The transmission characteristic may be selected from the group comprising field of view, frame rate, resolution, and compression.01-21-2010
20130013132AUTOMATIC PARAFOIL TURN CALCULATION METHOD AND APPARATUS - A method is described that involves performing the following with a parafoil's control unit composed of electronic circuitry while the control unit is being transported with a parafoil: determining a desired exit of a turn; determining a desired time for the turn; determining the parafoil's actual entrance for the turn; determining an arc between the actual entrance and the desired exit; and, incorporating said arc as said parafoil's planned flight trajectory through said turn.01-10-2013
20090105892TELEMETRY ANALYSIS SYSTEM NETWORKED DATA ACQUISITION SYSTEM - The present invention is, in its various aspects and embodiments, a method and apparatus for use in acquiring telemetry regarding an airborne vehicle. In one aspect, the processing of acquired telemetry data is distributed to the points of acquisition rather than at the host station. In another aspect, various points on the telemetry acquisition system employ a common network interface through which the telemetry acquisition stations communicate acquired telemetry data to the control station. In still another aspect, the invention also includes a TDP/IP protocol for communicating between stations. Still other aspects and embodiments are disclosed and claimed.04-23-2009
20110118906DISTRIBUTED FLIGHT CONTROL SYSTEM - A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.05-19-2011
20110118905METHODS SYSTEMS AND APPARATUS FOR ANALYZING COMPLEX SYSTEMS VIA PROGNOSTIC REASONING - Methods and apparatus are provided for analyzing a complex system that includes a number of subsystems. Each subsystem comprises at least one sensor designed to generate sensor data. Sensor data from at least one of the sensors is processed to generate binary evidence of a sensed event, and complex evidence of a sensed event. The complex evidence has more sophisticated mathematical properties than the binary evidence. The complex evidence comprises one or more of: a condition indicator (CI), a health indicator (HI), and a prognostic indicator (PI). A system fault model (SFM) is provided that defines statistical relationships between binary evidence, complex evidence, and an underlying failure mode (FM) that is occurring in the complex system. The binary evidence and the complex evidence are processed to identify failure modes taking place within one or more of the subsystems. Based on the binary evidence and the complex evidence and the SFM, diagnostic conclusions can be generated regarding adverse events that are taking place within the complex system, and prognostic conclusions can be generated regarding adverse events that are predicted to take place within the complex system.05-19-2011
20120310450METHODS AND SYSTEMS FOR BRIEFING AIRCRAFT PROCEDURES - Methods and systems are provided for providing procedure information associated with an aircraft procedure onboard an aircraft. An exemplary method involves obtaining a briefing sequence for the aircraft procedure and providing the procedure information via the output device, wherein the procedure information is provided in accordance with the briefing sequence. When the output device is realized as an audio output device, the procedure information is sequentially provided auditorily via the audio output device. In one or more embodiments, the procedure information is sequentially indicated on a display device onboard the aircraft in concert with the auditorily provided procedure information.12-06-2012
20120310449STRUCTURAL HEALTH MANAGEMENT WITH ACTIVE CONTROL USING INTEGRATED ELASTICITY MEASUREMENT - A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event.12-06-2012
20120310448AIRCRAFT ENVIRONMENTAL THREAT DETECTION AND MITIGATION - A method of aircraft engine thermal threat mitigation includes detecting an airflow thermal profile at a location on the aircraft forward of an aircraft engine inlet and transmitting the thermal profile to an aircraft control system. The thermal profile is compared to a catalog of thermal threat profiles at the aircraft control system and a determination is made if a thermal threat is present based on the comparison. A thermal threat mitigation measure is initiated to reduce an effect of the thermal threat on aircraft engine performance.12-06-2012
20110307125METHOD OF MONITORING THE EFFECTIVENESS OF A DAMPER, AND A DEVICE FOR IMPLEMENTING SAID METHOD - The present invention relates to a method of monitoring the effectiveness of a damper system, wherein the method consists in measuring the relative movements of two strength members, in filtering the measurements in order to isolate those that relate to the lead-lag resonant frequency of the blade, in rectifying the signal, in recording the signal, in comparing the rectified signal (S) with a threshold value (S12-15-2011
20100004800Method and system for resolving traffic conflicts in take-off and landing - A method and system for resolving existing and potential traffic conflicts that may occur during take-off and landing in aviation that includes means of monitoring movements on the runway, its approaches and environs to determine whether a conflict or potential conflict exists, means to resolve a conflict and to generate an output pertaining to this resolution.01-07-2010
20110276199FLIGHT CONTROL SYSTEM AND AIRCRAFT COMPRISING IT - A flight control system for an aircraft, in which control commands are transmitted between a flight control module (11-10-2011
20110276198VERTICAL PROFILE DISPLAY WITH VARIABLE DISPLAY BOUNDARIES - A display system includes instrumentation configured to obtain aircraft data comprising current flight status data of the host aircraft and current flight status data of neighboring aircraft located near the host aircraft. The system also includes a processor coupled to the instrumentation. The processor analyzes and filters the aircraft data, using lateral boundary criteria for the host aircraft, to identify a proper subset of the neighboring aircraft, and the processor generates image rendering display commands based upon the current flight status data of the host aircraft and based upon the current flight status data of neighboring aircraft included in the proper subset. A display element receives the image rendering display commands and, in response thereto, renders a vertical situation display that includes graphical representations of the host aircraft and each neighboring aircraft included the proper subset.11-10-2011
20120041620SYSTEMS AND METHODS FOR PROVIDING SPOOF DETECTION - Spoof detection can be performed by various systems and methods. The systems and methods can provide for detection by passive listening, active interrogation, and other techniques. Moreover, systems and methods can also provide for reporting and displaying information relating to detected spoofing. For example, a method can include receiving, on a device, a signal providing a report for an aircraft. The method can also include determining, with the device, a first parameter for the aircraft from information in the report. The method can further include determining, with the device, a second parameter for the aircraft from at least one signal characteristic of the signal. The method can additionally include determining, with the device, a validity status of the report based on comparing the first parameter and the second parameter.02-16-2012
20120065816SYSTEMS AND METHODS FOR DYNAMICALLY STABLE BRAKING - Systems and methods for dynamically stable braking are disclosed. A first electromechanical brake actuator controller may be placed in communication with a second electromechanical brake actuator controller, wherein each of the first electromechanical brake actuator controller and second electromechanical brake actuator controller are in communication with electromechanical brake actuators that are associated with the same wheel. The first electromechanical brake actuator controller and second electromechanical brake actuator controllers may then communicate electromechanical brake actuator status information and take corrective measures in accordance with the status information.03-15-2012
20120150365Wireless Precision Avionics Kit - A wireless precision avionics kit is provided for retrofitting aircraft to facilitate communication between the cockpit and modern military stores without hardware or software modifications to the aircraft. The store includes an electrical interface that requires data and possibly power from the aircraft and provides for communication via a message set. The kit may be used with any aircraft that provides a rack or pylon for mounting the store and the capability to release the store. The kit may be used with aircraft having no existing capability to communicate with smart stores, with aircraft having an incompatible interface for modern stores or even with aircraft that have a compatible hardware interface for which the software is outdated.06-14-2012
20090150012SYSTEM FOR PRODUCING A FLIGHT PLAN - A flight planning system includes one or more flight management system and a flight plan manager that constructs a flight plan according to static information from the flight management system. A flight management system that also constructs flight plans includes a flight plan manager that constructs a flight plan according to information stored in the flight management system. In constructing the flight plan, either flight management system may compute values of flight plan parameters, such as PNR, PET, ETOPS and LROPS, based on dynamic information related to the flight. On the ground, one of either type of flight management system is selected from a plurality thereof for producing a flight plan for a respective aircraft or aircraft model.06-11-2009
20120041619System for Aircraft - This invention relates to a sensing system with networking capabilities that is integrated into an aircraft that allows for rapid reconfiguration, monitoring, and access control of the aircraft by way of using fastening mechanisms, namely those with intelligent capabilities that provide sensing, control, and monitoring capabilities.02-16-2012
20090216392VECTORED THRUSTER AUGMENTED AIRCRAFT - The Invention is a rotary-wing aircraft having at least two vectored thrusters that may be tilted from a horizontal to a vertical position and to positions intermediate between the horizontal and vertical positions. The two vectored thrusters are equipped with propellers having separately variable pitch. The two vectored thrusters also are equipped with vanes having selectable vane angles to direct separately the air flow from the two vectored thrusters. A control system detects the flight condition of the aircraft and selects vectored thruster control settings corresponding to the detected flight condition and consistent with predetermined control rules to provide lift, thrust, yaw moments and roll moments.08-27-2009
20100100257Visual airport surface and terminal area data system - The invention supports the study of operations and provides a large data store of surface and terminal area operations, as well as means of analyzing and understanding that data. It fuses multiple surveillance and flight data sources to provide analysis functionality for both airborne and surface based flights. This provides a wider range of data to make intelligent categorization and derived data analysis decisions. The invention implements custom logic for matching flights to corresponding data messages by maintaining its own key mappings between data tables during import so that keys are unique to an installation and do not require sequences. This provides the ability to export datasets through the PostgreSQL dump utility and then import it into an existing database (using the PostgreSQL restore utility) without creating overlapping, duplicate or conflicting keys. XML based format is used and import and export features is that allow users to share these custom queries.04-22-2010
20090018714METHOD AND DEVICE FOR CONTROLLING THE THRUST OF A MULTI-ENGINE AIRCRAFT - The device (01-15-2009
20120046810FUZZY LOGIC-BASED CONTROL METHOD FOR HELICOPTERS CARRYING SUSPENDED LOADS - The fuzzy logic-based control method for helicopters carrying suspended loads utilizes a controller based on fuzzy logic membership distributions of sets of load swing angles. The anti-swing controller is fuzzy-based and has controller outputs that include additional displacements added to the helicopter trajectory in the longitudinal and lateral directions. This simple implementation requires only a small modification to the software of the helicopter position controller. The membership functions govern control parameters that are optimized using a particle swarm algorithm. The rules of the anti-swing controller are derived to mimic the performance of a time-delayed feedback controller. A tracking controller stabilizes the helicopter and tracks the trajectory generated by the anti-swing controller.02-23-2012
20120209456Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft - An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.08-16-2012
20120209455Autopilot with Adaptive Rate/Acceleration Based Damping - A control system includes a rate-damping loop that uses a motion parameter error (heading pitch, heading yaw, attitude pitch, attitude yaw, and attitude roll) to non-linearly scale a rate-feedback signal so that at lower motion parameter error values, an acceleration feedback term plays a greater role in pitch compensation, while at greater motion parameter error values, a rate-feedback term plays a greater role in the pitch compensation. In some embodiments, a control system and method of controlling a motion parameter of a moving body are provided. A signal representing a motion parameter error is non-linearly combined with a signal representing a rate-of-change of a motion parameter (or body angle) to generate a non-linear rate-damping signal. The non-linear rate-damping signal is subtracted from the signal representing the motion parameter error to generate a signal to control one or more elements of the moving body.08-16-2012
20100332053METHODS AND SYSTEMS FOR FAULT DETERMINATION FOR AIRCRAFT - A method for fault determination for an aircraft includes the steps of generating a predicted maneuver of the aircraft using an aircraft operating input and a model of aircraft performance, determining an actual maneuver of the aircraft using information obtained from an inertial measurement system, comparing the predicted maneuver and the actual maneuver, and determining a fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver.12-30-2010
20120116614METHOD AND APPARATUS FOR AIR TRAFFIC TRAJECTORY SYNCHRONIZATION - According to aspects of the embodiments, there is provided an apparatus and method to synchronize the distinct trajectories predicted by a flight management system and air navigation service provider. A comparison model is generated that indicates differences between an aircraft trajectory and a ground trajectory. The aircraft trajectory is updated to reflect identified discrepancies and restriction violations between the trajectories. Upon successful completion of the first designated change, a notification manager is used to issue a notification of the designated change to the flight plan trajectory. A modified ground trajectory is produced that incorporates the designated change to the flight plan trajectory. The comparison is repeated until the discrepancies of the trajector 05-10-2012
20120010765SYSTEM FOR DISPLAYING A PROCEDURE TO AN AIRCRAFT OPERATOR DURING A FLIGHT OF AN AIRCRAFT - A system is disclosed for displaying a procedure to an aircraft operator during a flight of an aircraft. The system includes, but is not limited to, a display unit, a data storage unit that is configured to store the procedure, an input unit, and a processor that is communicatively connected to the display unit, to the data storage unit and to the input unit. The processor is configured to obtain the procedure from the data storage unit, to receive an input from the input unit, and to control the display unit to display the procedure as a vertical profile having a compressed portion and an expanded portion, the expanded portion corresponding to the input.01-12-2012
20120016537System and Method for Detection of Anti-Satellite Vulnerability of an Orbiting Platform - A system and method for detection of anti-satellite vulnerability of an orbiting platform. An engagement volume processing unit receives a maximum impulse velocity of an SBI launched from a carrier platform of interest, a maximum time of flight (TOF) until intercept, and orbital data of the carrier platform of interest. A family of interceptor imparted velocities in a VNC frame is determined. The engagement volume processing unit applies the family of velocities over “N” release points using a carrier platform propagator to determine an engagement volume. A display and alert processing unit generates a visual representation of the engagement volume and sends the visual representation to the display device for display.01-19-2012
20120016538UAV POWER LINE POSITION AND LOAD PARAMETER ESTIMATION - A system and method for providing autonomous navigation for an Unmanned Air Vehicle (UAV) in the vicinity of power lines is presented. Autonomous navigation is achieved by measuring the magnitude and phase of the electromagnetic field at an unknown location within a space under excitation by a set of power cables of the power line with one or more orthogonal electromagnetic sensors formed on the UAV; modeling a set of expected complex electromagnetic strengths of the set of power cables at the currently estimated position and orientation of the UAV based on a model of the set of power cables; and estimating parameters related to a position and orientation of the UAV, and load parameters of each cable based on the residual error between the measured set of complex electromagnetic field values and the set of expected electromagnetic field values corresponding to a combined model of the set of power cables.01-19-2012
20120232722Automatic Configuration Control of a Device - Methods, systems, and devices for determining system/device configuration and setting a mode of operation based on the determined configuration. An air vehicle processor: (a) receives a component information 09-13-2012
20110046821Reconfigurable aircraft - A reconfigurable aircraft having a fuselage and a series of wing segments that form a wing, and an extra wing segment that is interchangeable with a wing segment that is part of the wing. The wing segments are readily attachable and detachable from the fuselage, allowing for the interchanging of the wing segments. At least one of the two interchangeable wing segments is configured with one type of mission-specific equipment, and the other may be configured with a second type of mission-specific equipment, allowing for the quick reconfiguration of the aircraft. Alternatively, the two interchangeable wing segments are each configured with the same mission-specific equipment, allowing for mission-specific equipment is serviced without interfering with the flight schedule. With an additional fuselage and set of wing segments that form a wing a mission may be continuously flown.02-24-2011
20120022721FLYING OBJECT - By using the interaction between the wind flow and the stabilizer arranged in the wind flow and along the direction of the wind flow, this invention provides the flying object that secures the stability of device or aircraft or stabilizer itself unified with the stabilizer by above effect. The interaction mentioned above is that when the wind flow hits the stabilizer at a certain angle, the wind flow changes the direction, and the power corresponding its reaction is given to the stabilizer by its reaction.01-26-2012
20120022722SYSTEMS, METHODS, AND APPARATUS FOR OTOACOUSTIC PROTECTION OF AUTONOMIC SYSTEMS - Systems, methods and apparatus are provided through which in some embodiments an autonomic unit transmits an otoacoustic signal to counteract a potentially harmful incoming signal.01-26-2012
20120022720METHOD AND DEVICE FOR PROTECTING SOFTWARE COMMANDS IN AN AIRCRAFT COCKPIT - The invention in particular has as an object the control of execution of software commands of a data-processing system in an aircraft cockpit comprising means for allowing a user to call up these commands. For these purposes, the means making it possible to call up these commands initially are locked (01-26-2012
20110093140DEVICE FOR DETERMINING THE POSITION OF A THROTTLE LEVER IN AN AIRCRAFT - A device for determining a position of a throttle lever includes position sensors each connected to a primary flight control computer, position sensors each connected to an engine management computer, the position sensors being split into at least three groups of sensors with no common simple failure mode, and at least one interface computer, that includes at least one input to receive measurement information emitted by the computers connected to the position sensors and outputs leading to the engine management computer.04-21-2011
20120116613METHOD OF CONTROLLING AN OVERSPEED SAFETY SYSTEM FOR AEROENGINES AND A CONTROL CIRCUIT FOR IMPLEMENTING SAID METHOD - A method of controlling an overspeed safety system for an aircraft having at least two engines. The method includes setting said overspeed safety system for the engines, monitoring the speeds of rotation of the engines, detecting overspeed on one of the engines, shutting down the engine in question in the event of detecting overspeed, and inhibiting the operation of the overspeed safety system for the other engine(s) still in operation. The method also comprises the steps of monitoring safety parameters associated with the operation and/or the shutting down of the engine that has been shut down; and maintaining the inhibition or resetting the overspeed safety system for the other engine(s) still in operation, as a function of one or more safety parameters.05-10-2012
20120123616SYSTEM AND METHOD FOR COMPUTING AN EQUI-TIME POINT FOR AIRCRAFTS - A system and method for generating an equi-time point (ETP) for an emergency landing of an aircraft are disclosed. In one aspect, a method of a flight management system (FMS) of an aircraft for generating an ETP for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency. The method also includes determining an equi-distance point (EDP) for the aircraft by locating a first point on the remaining flight path of the aircraft which is equidistant from the at least two reference points. The method further includes generating an ETP for the aircraft by locating a second point on the remaining flight path such that time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value.05-17-2012
20120158218STEERING ANGLE CONTROL SYSTEM FOR AIRCRAFT - To provide an aircraft steering angle control system that minimizes the amount of skidding of an airframe that is turning on a low-μ taxiway surface such as an icy taxiway surface and allows for directional control of the airframe by a steering command, an aircraft steering angle control system that outputs an operation signal related to a steering angle as a control command signal for a nose steering wheel incorporates a nose wheel envelope protection including a reference steering angle setting unit that calculates a reference steering angle on the assumption that the airframe is not skidding; a skid detection unit that detects a skidding state of the airframe based on the reference steering angle; and a switch unit that selects a control command signal for a nose wheel in conjunction with the skid detection unit.06-21-2012
20120158215Programmable Surface - In exemplary embodiments of this invention, a programmable surface comprises an array of cells. Each of the cells can communicate electronically with adjacent cells in the array, can compute, and can generate either normal thrust or shear thrust. Distributed computing is employed. The programmable surface may cover all or part of the exterior of a craft, such as an aircraft or marine vessel. Or, instead, the programmable surface may comprise the craft itself, which may, for example, take the form of a “flying carpet” or “flying sphere”. The thrust generated by the programmable surface can be employed directly to provide lift. Or it can be used to control the orientation of the craft, by varying the relative amount of thrust outputted by the respective cells. The number of cells employed may be changed on a mission-by-mission basis, to achieve “span on demand”. Each cell may carry its own payload.06-21-2012
20120158217DISTRIBUTED ACTIVE VIBRATION CONTROL SYSTEMS AND ROTARY WING AIRCRAFT WITH SUPPRESSED VIBRATIONS - A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween.06-21-2012
20120158216APPARATUS AND METHOD FOR AUTOMATICALLY GENERATING SATELLITE OPERATION PROCEDURE PARAMETERS - An apparatus for automatically generating satellite operation procedure (SOP) parameters is provided. The apparatus includes a parameter extraction unit configured to extract one or more SOP parameters corresponding to an SOP; a transformation formula extraction unit configured to extract a transformation formula corresponding to the extracted SOP parameters; and a calculation unit configured to calculate values of the extracted SOP parameters based on property information for performing a satellite task and the extracted transformation formula.06-21-2012
20120072057METHOD OF MANAGING MOVEMENT OF AN AIRCRAFT ON THE GROUND - The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.03-22-2012
20120072056FLIGHT CONTROL SYSTEM FOR ROTARY WING AIRCRAFT - A flight control system and method includes a control loop control law to bias the collective stick toward a trim reference position with a motor and generate a force gradient with a clutch.03-22-2012
20120109424AIRCRAFT CONTROL SYSTEM WITH INTEGRATED MODULAR ARCHITECTURE - An aircraft control system in which a plurality of elementary control systems, corresponding to different aircraft functions, can share one or more sensors due to a common AFDX network. The transmission of commands is carried out via AFDX messages sent to network-subscribed actuators. Advantageously, the computers of the different elementary control systems installed in the avionics bay include generic computers hosting software specific to execution of respective functions thereof (IMA architecture).05-03-2012
20100152926DYNAMIC ADJUSTMENT OF WING SURFACES FOR VARIABLE CAMBER - The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.06-17-2010
20110066305MULTI-AXIS SERIALLY REDUNDANT, SINGLE CHANNEL, MULTI-PATH FLY-BY-WIRE FLIGHT CONTROL SYSTEM - A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers.03-17-2011
20110106342Absolute angle correction apparatus - The instant invention provides an absolute angle correction apparatus for correcting flight angle and direction of a wireless aircraft. The absolute angle correction apparatus includes a controlling signal module, a microcontroller, a transducer module, an output module, and a power module for supplying power. The controlling signal module receives wireless signals from a remote controller, decoding the received wireless signals, and transferring to the microcontroller as original input values. The transducer module measures acceleration and attitude of the aircraft, and transfers measured values to the microcontroller as variation parameters. The microcontroller receives the original input values and the variation parameters, together calculates and outputs precisely computed results. The output module controls flight steering of the aircraft according to the computed result from the microcontroller. The absolute angle correction apparatus corrects flight angle and direction of the aircraft timely and accurately.05-05-2011
20100094485Computation-Time-Optimized Route Planning for Aircraft - A process and system for the planning a cost-minimized aircraft flight route between a starting point and end point takes into account costs associated with the flight route, no-fly zones and flight corridors, and aircraft limitations. A raster set is determined which comprises topographical points between the starting and end points, and costs associated with the respective raster points are determined. N nodes are determined for each raster point of at least one subset of the raster set, such nodes being associated with approach directions of the raster point by the aircraft. Possible take-off directions of the raster point are defined, taking into account the minimum turning radius of the aircraft, as a function of the approach direction. A cost-minimized flight route is determined by means of a shortest path algorithm, taking into account only the k most cost-effective nodes (k04-15-2010
20100094484INTEGRATING COMMUNICATION AND SURVEILLANCE - An aircraft control unit has modules for interfacing with various systems of an aircraft to integrate control of the systems. The modules include a communication module configured to be coupled to a communication system of the aircraft and a surveillance module configured to be coupled to a surveillance system of the aircraft. The aircraft control unit also includes a display screen for displaying information and a user interface usable to interact with the modules. Each of the modules is configured to display information on the display screen and to receive user input from the user interface.04-15-2010
20090132103SYSTEM FOR SECURING AN AIRCRAFT FLIGHT PLAN - The system for securing an aircraft flight plan has a flight management system delivering: a flight plan and points comprising passage setpoints in terms of speed, altitude and time; an avionics computer; at least one resource for storing environmental data constituting a hazard for the aircraft; a performance model of the aircraft defining limiting flight conditions according to the performance capabilities of said aircraft; at least one resource for processing the aircraft's avoidance trajectories. It makes it possible, based on a sampling of points of the flight plan, to calculate a set of avoidance trajectories and correlate them with the environmental data in order to detect the engagement points requiring a corrective maneuver.05-21-2009
20090210103Controlling aircraft aerial movements, defeating icing on aircraft surfaces, aiding decontamination, and damping turbulence effects on aircraft by the method of micro-perforated airfoil coordinated precision flow management - A method is provided whereby airplanes or any device with the functionality and usefulness of an airplane may be controlled without the use of any traditional effectors, such as flaps, rudders, ailerons, spoilers, and all like hinged, moveable airfoils attached to a wing or a fuselage. The means of controlling such airplanes while in flight will be by controlling the laminar air flow over all lifting surfaces so as to vary the amount and quality of the lift provided. All lifting surfaces on the airplane will be divided into dozens, hundreds, or thousands of small zones, each of which can be readily controlled by a central flight computer and each of which is capable of modifying its immediate airflow condition, whether that be laminar flow or some particular degree and variety of local eddy current. Summing over all the inputs of conditions above the multitude of zones, the central flight computer will possess algorithms and programs suitable to effect any desired change in attitude, altitude, orientation, and course of the airplane that is desired.08-20-2009
20100250026Interactive Navigation Device - The subject of the invention is an interactive navigation device comprising at least one navigation screen making it possible to display a graphical representation of at least one flight plan, a flight plan being composed of points and of segments. The device comprises means for displaying several flight plans simultaneously on the navigation screen at the same time as flight information text fields associated with the points of the said flight plans, the flight information fields being displayed in a manner contiguous with the points associated with them so as to be able to compare them conveniently. The device also comprises means for displaying on the navigation screen flight information fields associated with the segments of the flight plans, the said flight information fields being displayed in a manner contiguous with the segments associated with them.09-30-2010
20100250027METHOD TO REDUCE CARBON BRAKE WEAR THROUGH RESIDUAL BRAKE FORCE - The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs.09-30-2010
20100250025METHODS AND SYSTEMS FOR REVIEWING DATALINK CLEARANCES - Provided are methods and systems for the automatic assessment and presentation of data on a display device that describes the operational impact on mission critical parameters resulting from a change in a vehicle's mission plan. The change in mission plan may be inputted manually by the vehicle operator but may also be received electronically and automatically over a data up link from an outside authority.09-30-2010
20100250028SYSTEM AND METHOD FOR AIRCRAFT BRAKING SYSTEM USAGE MONITORING - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance traveled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal.09-30-2010
20120083947INTEGRATED FRAMEWORK FOR VEHICLE OPERATOR ASSISTANCE BASED ON A TRAJECTORY AND THREAT ASSESSMENT - Various types and levels of operator assistance are performed within a unified, configurable framework. A model of the device with a model of the environment and the current state of the device and the environment are used to iteratively generate a sequence of optimal device control inputs that, when applied to a model of the device, generate an optimal device trajectory through a constraint-bounded corridor or region within the state space. This optimal trajectory and the sequence of device control inputs that generates it is used to generate a threat assessment metric. An appropriate type and level of operator assistance is generated based on this threat assessment. Operator assistance modes include warnings, decision support, operator feedback, vehicle stability control, and autonomous or semi-autonomous hazard avoidance. The responses generated by each assistance mode are mutually consistent because they are generated using the same optimal trajectory.04-05-2012
20120083946TAILORED ARRIVALS ALLOCATION SYSTEM TRAJECTORY PREDICTOR - The different advantageous embodiments provide a system for generating trajectory predictions for a flight comprising a flight object manager and a trajectory predictor. The flight object manager is configured to generate flight information using a number of flight plans, a number of flight schedules, and flight status information. The trajectory predictor is configured to receive flight information from the flight object manager and use the flight information to generate the trajectory predictions.04-05-2012
20120215385AIRCRAFT SYSTEMS AND METHODS FOR PROVIDING EXHAUST WARNINGS - Aircraft system and method are provided for a first aircraft in an airport environment, the airport environment including a second aircraft. The system includes a sensor on the first aircraft configured to determine a temperature profile of engine exhaust from the second aircraft; and a processing unit coupled to the sensor and configured to construct a velocity profile of the engine exhaust from the second aircraft based on the temperature profile and to generate a warning for a pilot of the first aircraft based on the velocity profile.08-23-2012
20120130564SYSTEM AND METHOD FOR COMPUTING AN EQUI-DISTANCE POINT (EDP) FOR AIRCRAFTS - A system and method for dynamically computing an equi-distance point (EDP) for aircrafts is disclosed. In one embodiment, a method for dynamically computing an EDP for an aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency, determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by a flight management system (FMS) of the aircraft, and generating the EDP for the aircraft by locating a point on the remaining flight path which is equidistant from the at least two reference points.05-24-2012
20120130563SYSTEM AND METHOD FOR SELECTIVELY ENABLING A CONTROL SYSTEM FOR ACCESSING A CENTRAL PROCESSING UNIT - A system and method are disclosed for selectively enabling a control system using a biometric and a physiological sensor to determine the status of an operator. An input component is operatively coupled to the sensor to permit an operator to initialize the sensor. A central processor unit is operatively coupled to the operator sensor and the central processor unit has a transceiver operatively coupled therewith for processing and evaluating the biometric and physiological information: A transceiver coupled with a remote ground control; an override operatively coupled to the ground control. Alternatively, the present invention comprises a security control center, which controls the operation of at least one biometric sensor and at least on physiological sensor: the security control center also capable of detecting said normal and said abnormal sensory reading and the central processing unit in response to said sensory reading.05-24-2012
20120136512External Load Inverse Plant - A method of controlling the flight of a rotorcraft in a feed-forward/feedback architecture includes utilizing an aircraft plant model to control the rotorcraft performance; determining when an external load is coupled to the rotorcraft; and modifying an inverse plant when the external load is present.05-31-2012
20120136513Accelerometer autopilot system - The Accelerometer Autopilot System is an airplane and helicopter autopilot system that functions by a specially programmed software. The computer program directs aircraft navigation using accelerometer generated coordinates of altitude, latitude, longitude and distance travelled. The system uses four accelerometers that are specifically aligned by a solid-state compass to True North. Using fundamental Dynamics equations, the accellerations or decellerations are timed by an atomic clock and converted into velocities and distances. The distances are then either added to or subtracted from the departure point coordinates to obtain the new position coordinates. These new position coordinates will identify the real-time position of the aircraft as it is flying. When these coordinates are recorded during a programming flight the autopilot will track these coordinates as will be shown on the dashboard display screen. The pre-recorded coordinate course and the course azimuth will guide the aircraft to the destination point. This is accomplished without the use of gyros, GPS, or a VOR radio signal.05-31-2012
20120215386Method And Device For Aiding The Flight Management Of An Aircraft - Method and device for aiding the flight management of an aircraft. 08-23-2012
20110184591SYSTEM AND METHOD FOR DETERMINING CHARACTERISTIC PARAMETERS IN AN AIRCRAFT - The present invention provides a method and a calculation system for an aircraft, with at least one sensor for detecting aeroelastic and flight-mechanical momenta of the aircraft, for detecting positions and movements of control surfaces of the aircraft or for detecting speeds of gusts of wind acting on the aircraft and comprising a calculation unit which calculates characteristic quantities of passenger comfort and cabin safety as well as momenta of the aircraft as a function of the sensor data provided by the sensors and a non-linear simulation model of the aircraft.07-28-2011
20090292405WING-BODY LOAD ALLEVIATION FOR AIRCRAFT - A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.11-26-2009
20120221180UNMANNED AERIAL VEHICLE AND CONTROL METHOD THEREOF - A method for controlling an unmanned aerial vehicle (UAV) using a control device receives a first direction of the control device and a control command of the UAV, obtains a second direction of the UAV, and calculates an angle deviation between the first direction and the second direction. The method further adjusts the second direction of the UAV according to the angle deviation, and controls a flight direction of the UAV according to the received control command.08-30-2012
20120221179UNMANNED AERIAL VEHICLE AND METHOD FOR ADJUSTING FLIGHT DIRECTION OF THE SAME - A method for adjusting a flight direction of an unmanned aerial vehicle (UAV) using a control device receives a first direction of the control device and a control command of the UAV, obtains a second direction of the UAV, and calculates an angle deviation between the first direction and the second direction. The method further adjusts the control command of the UAV according to the angle deviation to obtain an adjusted control command, and controls a flight direction of the UAV according to the adjusted control command08-30-2012
20120173052Method And Device For Automatically Monitoring Air Operations Requiring Navigation And Guidance Performance - The monitoring device (07-05-2012
20110190964TURNING-STABILIZED ESTIMATION OF THE ATTITUDE ANGLES OF AN AIRCRAFT - The present invention relates to estimating the attitude angles of an aircraft (08-04-2011
20120259485EMERGENCY COMMUNICATIONS CHANNEL SYSTEMS AND METHODS FOR SATELLITE COMMAND - Systems and methods for commanding a satellite are provided. A system for commanding a satellite includes a data bus and a payload coupled to the data bus, the payload including a payload receiver. The system further includes a primary receiver coupled to the data bus and a processor coupled to the data bus. The processor configured to receive a first command from the primary receiver via the data bus, and to receive telemetry data from the payload via the data bus. The processor is further configured to detect a second command by processing the telemetry data received from the payload, and to execute the detected second command.10-11-2012
20120259484INFLATABLE PERSONAL RESTRAINT SYSTEMS - An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system.10-11-2012
20120259483ACTUATION CONTROL SYSTEM - A dual redundant actuation control system for controlling a plurality of actuators for positioning a plurality of moveable aircraft components. The actuation control system includes a component controller. The component controller includes two component control channels. Each of the plurality of actuators is electrically connected to each of the two component control channels such that either of the two component control channels may control any or all of the plurality of actuators.10-11-2012
20100049378METHOD AND DEVICE FOR ASSISTING IN THE PREPARATION AND MANAGEMENT OF MISSIONS IN AN AIRCRAFT - The invention in particular has as its object a method and a device for an aircraft for aiding in the preparation and management of missions. After a plurality of digital data has been received (02-25-2010
20100049379METHOD AND DEVICE FOR ASSISTING IN THE DIAGNOSTIC AND IN THE DISPATCH DECISION OF AN AIRCRAFT - The invention has as its object in particular a method and a device for aiding in the diagnosis and in the decision on operation of an aircraft comprising means for detection of failures relating to the pieces of equipment thereof. After having received (02-25-2010
20100274418Method for Determining the Quantity of Fuel Taken On Board an Aircraft Making it Possible to Maintain a Time Requirement of the RTA Type - A method for determining the quantity of fuel in an aircraft and an optimization criterion such as a cost index, notably used in an FMS, making it possible to maintain a time requirement of the RTA type, comprising a first step of computing the optimization criterion CI10-28-2010
20100274416DISTRIBUTED APPROACH TO ELECTRONIC ENGINE CONTROL FOR GAS TURBINE ENGINES - A distributed electronic engine control system includes an airframe module, an electronic engine control module, and an engine I/O module. The modules are arranged in locations remote from one another. A serial communications bus interconnects the modules with one another. A first engine controls device is connected to the engine I/O module and is configured to interact with an engine component and provide a first data. The engine I/O module includes inner loop control logic that uses the first data and produces a second data in response thereto. The electronic engine control module includes an outer loop control logic using the second data and produces a third data in response thereto. The airframe module receives power and distributes the power to the electronic engine control and engine I/O modules. The first, second and third data are provided on the serial communications bus.10-28-2010
20100274415TIME-TO-GO MISSILE GUIDANCE METHOD AND SYSTEM - A method and apparatus for guiding a vehicle to intercept a target is described. The method iteratively estimates a time-to-go until target intercept and modifies an acceleration command based upon the revised time-to-go estimate. The time-to-go estimate depends upon the position, the velocity, and the actual or real time acceleration of both the vehicle and the target. By more accurately estimating the time-to-go, the method is especially useful for applications employing a warhead designed to detonate in close proximity to the target. The method may also be used in vehicle accident avoidance and vehicle guidance applications.10-28-2010
20120179307APPARATUSES AND METHODS FOR DISPLAYING AND RECEIVING TACTICAL AND STRATEGIC FLIGHT GUIDANCE INFORMATION - Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information are disclosed. A method in accordance with one aspect of the invention includes displaying at least one first indicator to an operator of the aircraft, with a first indicator corresponding to a first instruction input by the operator for directing a first aircraft behavior and implemented upon receiving an activation instruction from the operator. At least one second indicator corresponding to a second instruction for directing a second aircraft behavior at least proximately the same as the first aircraft behavior is displayed, with the at least one second instruction to be automatically implemented at a future time. The at least one second indicator is at least approximately the same as the at least one first indicator. Indicators can be hierarchically organized to simplify presentation and reduce pilot training time.07-12-2012
20100268404METHOD AND SYSTEM TO INCREASE ELECTRIC BRAKE CLAMPING FORCE ACCURACY - The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force.10-21-2010
20090062972Systems and Methods for Presenting and Obtaining Flight Control Information - Systems and methods for presenting and obtaining flight control information are disclosed. In one embodiment, information corresponding to a vertical motion of the aircraft can be displayed between information corresponding to a lateral motion of the aircraft and information corresponding to an airspeed of the aircraft. The information displayed can include a current mode for controlling the motion of the aircraft, a current target to which the aircraft is being directed and, at least proximate to both the current mode and the current target, a subsequent target to which the aircraft will be directed after attaining the current target.03-05-2009
20120253559Method And Device For Automatically Detecting Erroneous Air Data On An Aircraft - The device (10-04-2012
20120253560METHOD AND A DEVICE FOR ASSISTING THE PILOTING OF AN AIRCRAFT, AND AN AIRCRAFT - A method of assisting the piloting of an aircraft (10-04-2012
20120253557SYSTEMS AND METHODS FOR CONTROLLING THE SPEED OF AN AIRCRAFT - A system is provided for controlling the speed of an aircraft with a speed brake during flight. The system includes a guidance system configured to determine a target speed for the aircraft; a speed brake control system coupled to the guidance system and configured to compare the target speed to a current speed to generate speed brake guidance; and a display unit coupled to the speed brake control system and configured to display a visual representation of the speed brake guidance to a pilot of the aircraft.10-04-2012
20120253558Flight Control Laws for Constant Vector Flat Turns - An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed.10-04-2012
20120253555METHODS AND SYSTEMS FOR TRANSLATING AN EMERGENCY SYSTEM ALERT SIGNAL TO AN AUTOMATED FLIGHT SYSTEM MANEUVER - Systems, methods and apparatus are provided for translating an alert signal into an auto flight system (AFS) maneuver. The system comprises a first module. The first module is configured to receive an alert signal and to construct one or more AFS mode commands associated with the alert signal. The system also comprises a second module. The second module is configured to read and to execute the one or more AFS mode commands that when executed manipulate two or more standard AFS modes that implement the AFS maneuver. The system further comprises a state machine, which couples the first module to the second module and is configured to coordinate the construction of the one or more AFS mode commands by the first module with an execution of the one or more AFS mode commands by the second module.10-04-2012
20080312778SERVER DESIGN AND METHOD - A communication system for a vehicle includes a server that includes a real time operating system, at least one cabin function application that runs on the real time operating system, and at least one in-flight entertainment application that runs on another operating system on top of the real time operating system. Thus, an in-operation entertainment system is capable of providing audio and/or visual content to a large number of locations in a cabin of the vehicle, and a cabin function system is capable of providing various cabin applications, e.g., lighting level control, attendant calling, air conditioning control, etc. at different locations in the vehicle cabin in a manner that is isolated and prioritized over the entertainment system.12-18-2008
20120232721DUAL-AIRCRAFT ATMOSPHERIC PLATFORM - A platform including two winged aircraft are tethered during flight by a single tether near their respective centers of gravity. The tether is windable about a reel, so that a distance between the aircraft can be changed during flight. The aircraft contain avionics configured to enable autonomous flight using natural wind gradients. One aircraft imposes aerodynamic forces on the other, through the tether, while flying at an altitude where wind speed is significantly different than wind speed at an altitude of the other aircraft. The two aircraft cruise back and forth within a maximum distance from a station on the ground. Cruise conditions are established using an iterative computer algorithm which utilizes flight measurements. The aircraft communicate information between each other, and the ground, and contain a payload which performs a useful function at high altitudes.09-13-2012
20080300737METHOD AND DEVICE FOR CALCULATING A FLIGHT PLAN - The invention relates to a method for calculating a diversion flight plan making it possible to define at least one diversion airport to have the associated predictions on the corresponding diversion flight plan. The invention also relates to a device comprising means implementing the method according to the invention. The device according to the invention makes it possible to change, in the course of the flight, the said waypoint from which the diversion flight plan is calculated. The method according to the invention furthermore calculates the last possible diversion point on the flight plan, based on the fuel predictions.12-04-2008
20080300736SYSTEM AND METHOD FOR CONTROLLING THE SPEED OF AN AIRCRAFT - A system and method are disclosed for controlling the speed of an aircraft having a preprogrammed speed profile when transitioning from a manually set target speed to the preprogrammed speed profile. In operation, an input is received indicating that a user desires to transition from a manually set target speed to the preprogrammed speed profile. A determination is then made as to whether the manually set target speed satisfies one or more selected conditions for qualifying as a constraint speed of the preprogrammed speed profile. If the manually set target speed satisfies the one or more selected conditions, the preprogrammed speed profile is updated to include the manually set target speed as a constraint speed and the speed of the aircraft is controlled using the updated speed profile.12-04-2008
20080300735TERRAIN AUGMENTED DISPLAY SYMBOLOGY - Terrain augmented display symbology improves a pilot's spatial awareness during aircraft approach and landing. The symbology includes a terrain-tracing, three-dimensional centerline that provides a visual cue of terrain elevations along an approach course to a runway. Additionally, the symbology includes terrain-tracing, three-dimensional lateral deviation marks representing deviations from the centerline. The symbology also includes an aircraft symbol shaped like an airplane and pointing towards the direction of travel. The pilot may be able to quickly interpret the terrain augmented display symbology and take actions based on the surrounding terrain elevation.12-04-2008
20120239227Variable Maximum Commandable Roll Rate for Directional Control During Engine-Out Rolling Maneuver - A system and a method for varying a maximum roll rate command for ensuring sufficient directional control during an engine-out rolling maneuver of a multi-engine aircraft. For a multi-engine airplane with a roll rate command flight control system, the primary flight control computer is used to vary the maximum commandable roll rate to preserve the desired control margins during roll maneuvers where the rudder is fully deflected to control a thrust asymmetry. When the engine-out yawing moment exceeds a specified value, the system sets a reduced limit on the amount of roll rate the pilot can command.09-20-2012
20120239228APPARATUS AND METHOD FOR CONTROLLING POWER GENERATION SYSTEM - A vehicle includes at least one propulsion member and a power generation system. The power generation system includes a power source and a transmission configured to provide torque to the at least one propulsion member. The power generation system further includes a control apparatus comprising an input device and a processor. The processor is configured to receive signals indicative of a power output command, a plurality of detected ambient air conditions, and a plurality of detected power generation system parameters. The processor is also configured to determine a plurality of power generation system control settings for improving efficiency of the vehicle based on at least one of signals indicative of the power output command, the signals indicative of the plurality of detected ambient air conditions, and the signals indicative of a plurality of power generation system parameters.09-20-2012
20120330482METHOD OF CONTROLLING THE STEERING OF A STEERABLE PORTION OF AN AIRCRAFT UNDERCARRIAGE - The invention relates to a method of controlling the steering of a steerable portion of an aircraft undercarriage that is fitted both with a steering member for steering the steerable portion and also with at least two angular position sensors for sensing the angular position of the steerable portion in order to deliver respective signals representative of the angular position of the steerable portion, wherein the steering member is controlled by means of servo-control using information that is representative of the angular position of the steerable portion. According to the invention, the information representative of the angular position that is used is a mean of the angular positions sensed by the at least two angular position sensors.12-27-2012
20120323410FATIGUE MANAGEMENT SYSTEM - A fatigue management system for determining the individual life of an aircraft, particularly the individual life of components of a helicopter, by means of an on board virtual load sensor and a method of operating a fatigue management system.12-20-2012
20120271491CAPTURING ENVIRONMENTAL INFORMATION - In general, a method performed on a vehicle includes determining that the vehicle is located within a predetermined range of a beacon, the beacon being associated with a beacon identification, navigating the vehicle to a first location based on determining that the vehicle is located with the predetermined range, generating a first report based on determining that the vehicle is located at the first location, the generating including: specifying the beacon identification, recording navigation data that includes an altitude, a distance from the beacon, and a bearing relative to the beacon, and recording environmental data. The method further includes transmitting the first report from the vehicle to a base station, the first report including the beacon identification, the navigation data, and the environmental data.10-25-2012
20120323409Dynamically Reconfigurable Electrical Interface - A dynamically reconfigurable electrical interface is disclosed that can be used in various applications, including avionics communications. In one embodiment, a first switch receives an input signal and routes it to the applicable signal conditioning path unit that conditions the input signal, after which a second switch routes it to an amplifier. The amplifier provides an amplified signal to an analog-to-digital converter that generates a corresponding numerical value based on the voltage of the amplified signal that is analyzed by a processor to determine information conveyed by the input signal based on a particular electrical interface. Multiple distinct interfaces can be accommodated by on one more processors accessing instructions sets for processing information corresponding to a particular electrical interface. In another embodiment, the processor provides numerical values to a digital-to-analog converter producing an analog signal that is amplified, routed, and conditioned to convey information using a particular electrical interface.12-20-2012
20100228406UAV Flight Control Method And System - Disclosed herein is a method and system for flying a ducted-fan air-vehicle, such as an unmanned air-vehicle. The method includes receiving a first input associated with a target point of interest and pointing the gimbaled sensor at the target point of interest. The method further includes receiving a second input corresponding to a desired flight path and selecting a velocity vector flight command to achieve the desired flight path. Selecting the velocity vector flight command includes converting attitude data from the gimbaled sensor into a velocity vector flight command. The method further includes operating the flight of the UAV according to the selected velocity vector flight command and the gimbaled sensor remains fixed on the target point of interest during the flight of the UAV.09-09-2010
20100131125METHOD FOR ASSISTING IN THE MANAGEMENT OF THE FLIGHT OF AN AIRCRAFT IN ORDER TO KEEP TO A TIME CONSTRAINT - The invention relates to the field of civil aviation and, more specifically, relates to the flight management systems, more commonly known by the English acronym FMS. The method for assisting in the management of the flight of an aircraft in order to keep to a time constraint according to the present invention allows for a control of the keeping to the time constraint that presents a rapid dynamic, by avoiding as far as possible having the estimated time of arrival (ETA) at a particular point (P) able to drift relative to a required time of arrival (RTA) at said particular point (P), thanks to the use of a manoeuvring margin (M) granted to the guidance module of the aircraft.05-27-2010
20110238239Single Processor Class-3 Electronic Flight Bag - An electronic flight bag providing computational services for an aircraft and communicating with aircraft avionics may execute aircraft-design-approved Type-C applications together with non-design-approved Type-A/B on a single processor through specific modifications of the operating system to control memory and processor access thereby providing isolation comparable to that of dual processor systems in which the Type-C applications and Type-A/B applications are executed on different processors.09-29-2011
20120130565FLIGHT CONTROL SYSTEM OF AIRCRAFT - A flight control system of an aircraft and a flight control method of the aircraft are provided in which the overrunning an operation limitation on a flight condition can be prevented even when a pilot operates a flight control device fast. The flight control system of the aircraft includes a flight control device; a sensor configured to detect a first parameter changed based on a flight condition of the aircraft; a limitation flight control position calculating section configured to calculate a limitation flight control position of the flight control device when the first parameter reaches a limitation value, based on the first parameter; a reaction force generating actuator configured to change a reaction force which the pilot receives when carrying out a flight control input to the flight control device, in response to a reaction force generating command generated based on the flight control position of the flight control device and the limitation flight control position; an inner loop command calculating section configured to generate an inner loop command based on the flight control position; and a control surface actuator configured to drive a control surface of the aircraft based on the flight control position and the inner loop command.05-24-2012
20120089277VARIABLE GAIN CONTROL NOSE WHEEL STEERING SYSTEM - A method for determining a target steering angle for nose landing gear of an aircraft includes receiving rudder pedal input data into a steering control unit, receiving aircraft speed data into the steering control unit, calculating a normal gain, calculating a parking gain, and adding the normal gain and the parking gain to determine the target steering angle. The normal gain is a positive quantity in all aircraft speed and pedal stroke ranges. The parking gain is a positive quantity in parking and taxiing speed ranges. A nose wheel steering system is also disclosed.04-12-2012
20120101666Aircraft Occupant Protection System - An occupant protection system for an aircraft comprising a sensor system for sensing flight condition information and a control system, which includes an impending crash detection system and an impact detection system. The impending crash detection system receives flight information from the sensors determines whether a crash is likely to occur. If an impending crash is detected, the impending crash detection system activates impact modes of a first group of aircraft systems. The impact detection system receives flight information from the sensor system and determines whether an impact has occurred or is occurring. If an impact is detected, the impact detection system activates impact modes of a second group of aircraft systems.04-26-2012
20120101665VEHICLE INTERFACE BASED ON THE WEIGHT DISTRIBUTION OF A USER - In one embodiment, the invention is an interface for communicating a vehicle command from a user to a vehicle. The interface preferably includes a support system to support at least a portion of the weight of a user, a sensor system to sense the weight distribution of the user, and a processor to interpret a vehicle command based on the weight distribution of the user and to communicate the vehicle command to a vehicle.04-26-2012
20120101664Method of Controlling Steering Control Equipment for Aircraft, and Steering Control Equipment for Aircraft and Aircraft Provided Therewith - A steering control equipment has a controller having a provisional-target-angular-position calculating section calculating a provisional target angular position of a steering mechanism corresponding to the operation amounts of a steering handle and rudder pedals, a speed setting section setting the aircraft speed on the basis of detected ground speed and airspeed, a target-angular-position limiting section outputting the provisional target angular position as a final target angular position when the calculated provisional target angular position is equal to or lower than a limit value corresponding to the set speed and outputting the limit value as a final target angular position when the calculated provisional target angular position is larger than the limit value, and a actuating control section controlling an actuating mechanism for actuating the steering mechanism so that the output final target angular position and the actual angular position of the steering mechanism detected coincide with each other.04-26-2012
20120101663DISTRIBUTED FLIGHT CONTROL SYSTEM IMPLEMENTED ACCORDING TO AN INTEGRATED MODULAR AVIONICS ARCHITECTURE - A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.04-26-2012
20100198431MAINTENANCE COMPUTER SYSTEM FOR AN AIRCRAFT - A maintenance computer system for an aircraft, including a network partitioned into a secured avionics zone and an open zone. The system includes a first software module accommodated in the avionics zone and a second software module accommodated in the open zone, the first module configured to follow a fault-finding logic tree, and the second module configured to present an electronic maintenance document, with the path along the fault-finding logic tree followed by the first module automatically and synchronously generating a presentation by the second module of pages of the maintenance document associated respectively with nodes of the tree.08-05-2010
20130013131METHOD AND APPARATUS FOR PARAFOIL GUIDANCE THAT ACCOUNTS FOR GROUND WINDS - A method is described that involves determining a higher altitude wind. The method further includes determining a wind model with the higher altitude wind. The wind model includes a linear or logarithmic increase in wind magnitude with increasing altitude beneath the higher altitude. The method further includes determining locations of a flight path for a parafoil based on calculations that use the wind model. The calculations are performed by an electronic control unit that is transported by the parafoil. The method also includes controlling the parafoil's flight path consistently with the determined locations. The controlling is performed by the control unit.01-10-2013
20120150367Method And Device For Automatically Monitoring The Ability Of An Aircraft To Follow A Flight Trajectory With At Least One Turn - Method and device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn.06-14-2012
20120150366Method And Device For The Passivation Of Guidance Orders Of An Aircraft - The device (06-14-2012
20120150364UNMANNED VEHICLE AND SYSTEM - An unmanned vehicle is provided. The unmanned vehicle includes a navigation system configured to navigate the unmanned vehicle relative to a beam of energy emitted from a beam source, a power receiver configured to receive energy from the beam, and an energy storage system configured to store received energy for use in selectively powering the unmanned vehicle.06-14-2012
20130018532SOLAR ENERGY COLLECTION FLIGHT PATH MANAGEMENT SYSTEM FOR AIRCRAFTAANM Segal; Matthew JonathanAACI CalabasasAAST CAAACO USAAGP Segal; Matthew Jonathan Calabasas CA USAANM Wise; Kevin AndrewAACI St. CharlesAAST MOAACO USAAGP Wise; Kevin Andrew St. Charles MO US - A method and apparatus for managing solar power collection. A position of the sun is identified relative to an aerospace vehicle while the aerospace vehicle is moving along a flight path. A level of power generation is identified by a solar power generation system while the aerospace vehicle moves along the flight path using a threat management module and equivalent radar signature data. The threat management module uses the equivalent radar signature data to identify the level of power generation by the aerospace vehicle from different positions of the sun relative to the aerospace vehicle, and the equivalent radar signature data is based on solar power generation signature data identifying the level of power generation for the different positions of the sun relative to the aerospace vehicle. A change in the flight path that results in a desired level of power generation is identified by the solar power generation system.01-17-2013
20110160938DEVICE FOR CENTRALIZED MANAGEMENT OF TASKS TO BE CARRIED OUT BY A CREW OF AN AIRCRAFT - The present invention relates to a device for centralized management of tasks to be carried out by a crew of an aircraft. A task to be carried out includes a triggering condition and an instruction to be executed. The device includes a man-machine interface for managing tasks by the crew, a module for creating, modifying, deleting tasks, a module for triggering a task, a module for acknowledging a task performed, a module for executing a task, and an interface with systems of the aircraft which are able to create and to execute tasks. The invention applies to the piloting tasks carried out by the pilots of an aircraft.06-30-2011
20110160937METHOD AND DEVICE FOR CENTRALIZED MANAGEMENT OF TASKS TO BE CARRIED OUT BY A CREW OF AN AIRCRAFT DURING FLIGHT - The present invention relates to a method and a device for centralized management of tasks to be carried out by a crew in the course of an aircraft flight. The method uses onboard navigation aid systems, such as a flight management system, a system for managing in-flight alerts for the implementation of the following steps: creation of a task by the flight management system; scheduling of the tasks by a system for managing alerts; and task execution by the system for managing alerts.06-30-2011
20110160936METHOD AND DEVICE FOR ACCESSING THE DOCUMENTATION OF AN AIRCRAFT ACCORDING TO ALARMS GENERATED THEREIN - The invention in particular has as an object a method and a device for accessing the documentation of an aircraft according to alarms generated therein, the documentation comprising at least one document modifiable independently of the manufacturer of the aircraft. After having received (06-30-2011
20130024051DEVICE AND METHOD FOR REGULATING THE HUMIDITY OF A FUEL CELL - A device and a method for controlling the air humidity in a fuel cell detect a step response in the output voltage of a fuel cell when the supply to electrical loads is interrupted, and determine parameters of the dynamic time characteristic from the detected step response, and thus calculate a capacitance of the fuel cell. As a function of any deviation from a predetermined capacitance, a humidity control unit is caused to increase or decrease the humidity. This makes in situ detection of the humidity balance of a fuel cell possible, and this can keep the electrical power thereof constant for a relatively long period, and this can increase the intervals between maintenance.01-24-2013
20130024050ON-BOARD MAINTENANCE SYSTEM OF AN AIRCRAFT, AND ASSOCIATED AIRCRAFT - An on-board maintenance system for an aircraft, said aircraft comprising pieces of equipment connected together through a first on-board data transmission network for exchanging operational data intended for piloting the aircraft, said maintenance system including a processing unit and being characterized in that it comprises a second data transmission network, distinct from the first network, for exchanging data intended for maintenance of the equipment of the aircraft, said second network connecting at least some of said pieces of equipment to the processing unit; said processing unit are being adapted for receiving in real time, a data provided by the pieces of equipment on the second network and processing them with view to determining the cause of equipment malfunctions according to at least said received data.01-24-2013
20130173090Aircraft Flight Management Aid Device - A configured aircraft flight management aid system comprises: means of interpretation receiving data taken from external instructions from an external control center, data relating to aircraft equipment failures, cabin problems and problems related to the environment of the aircraft; means of determination receiving data from the means of interpretation and determining at least one reference constraint associated with at least one parameter representative of a flight path, a reference constraint associated with a reference parameter comprising a new constraint, different from the initial constraint when the item of data effectively necessitates following a new path, different from the initial path, and a reference constraint comprising the initial constraint when the means of determination do not have access to any data relating to an event effectively necessitating following a new path; warning means generating a warning to an operator when the path actually flown does not comply with said reference constraint.07-04-2013
20090143924SYSTEMS AND METHODS FOR ARBITRATING SENSOR AND ACTUATOR SIGNALS IN A MULTI-CHANNEL CONTROL SYSTEM - Systems and methods are provided for arbitrating sensor and actuator signals in various devices. One system includes input/output (I/O) circuitry, redundant computation circuits coupled to the I/O circuitry, and an arbitration circuit coupled between the I/O circuitry and the redundant computation circuits. The I/O circuitry is configured to be coupled to multiple non-redundant systems, and the redundant computation circuits are configured to be coupled to one of multiple system buses. One such device is an aircraft including multiple non-redundant systems and a plurality of system buses that are configured to transmit redundant messages to the non-redundant systems. A method includes receiving notice that redundant control signals have been received by multiple computation circuits, determining the health of each computation circuit, selecting a computation circuit from which to receive a control signal based on its health level, and transmitting the control signal from the selected computation circuit to I/O circuitry.06-04-2009
20080234879GROUND FAULT INTERRUPTION USING DSP BASED SSPC MODULE - A ground fault interruption (GFI) system is incorporated onto a DSP based LRM of an aerospace vehicle. The GFI system operates with digital controls and, unlike the prior art, the system does not employ current transformers. Synchronization pulses are employed to coordinate instantaneous current measurement samplings in each phase of a multi-phase power system. Coordinated sampling may reduce phase angle current differential errors and improve operational precision of the GFI system.09-25-2008
20080228331SYSTEM AND METHOD FOR MEASURING PARAMETERS AT AIRCRAFT LOCI - A system for measuring parameters at a plurality of loci associated with an aircraft includes: (a) a central unit; (b) a plurality of communicating nodes coupled with the central unit; and (c) a respective plurality of sensing units associated with each respective communicating node of the plurality of communicating nodes; at least one selected sensing unit of at least one respective plurality of sensing units being a remote sensing unit. The at least one remote sensing unit communicates wirelessly with the respective communicating node.09-18-2008
20080228330On-Demand Flight Data Service - A flight data service subscription system allows personnel to subscribe to flight data services using an electronic devices such as a multifunctional display (MFD) onboard an aircraft. The MFD is used to select regional areas of coverage and generate requests for subscriptions to flight data services. Flight data application software running on the MFD manages flight data and the subscription requests. A server operated by a flight data service provider receives the subscription requests from the MFD and dispatches flight data responsive to the requests for the selected region. A wireless local area network on the ground transfers flight data and subscription requests between the MFD and the flight data subscription server.09-18-2008
20080221745COLLECTION AND DISTRIBUTION SYSTEM - A collection and distribution system wherein information is collected from one or more aerial vehicles and from one or more ground-based sources before being processed and provided to an end-user.09-11-2008
20130179009Auto-Flight System Pilot Interface - An aircraft system comprising a display system, a graphical user interface, a first grouping of the controls in the graphical user interface, and a second grouping of the controls in the graphical user interface. The graphical user interface is configured to display controls on the display system. The controls are for commands sent to an auto-flight system in an aircraft that control flight of the aircraft. The first grouping of the controls is configured to control sending of the commands to the auto-flight system from a flight management system in the aircraft. The second grouping of the controls is configured to control sending of the commands to the auto-flight system from a user input to the graphical user interface.07-11-2013
20130179008USING PREDICTED MOVEMENT TO MAINTAIN OPTICAL-COMMUNICATION LOCK WITH NEARBY BALLOON - A balloon may include an optical-communication component, which may have a pointing axis. A pointing mechanism could be configured to adjust the pointing axis. The optical-communication component could be operable to communicate with a correspondent balloon via a free-space optical link. For example, the optical-communication component could include an optical receiver, transmitter, or transceiver. A controller could be configured to determine a predicted relative location of the correspondent balloon. The controller may control the pointing mechanism to adjust the pointing axis of the optical-communication component based on the predicted relative location so as to maintain the free-space optical link with the correspondent balloon.07-11-2013
20120253561RESPONSE MODE FOR CONTROL SYSTEM OF PILOTED CRAFT - Frequency multiplexed command signaling that permits a single pilot command interface (e.g. control stick) to serve as a multiple response mode interface for piloting a craft conforms with natural interface operation of most pilots. Highly augmented modes receive lower frequency components of the command signaling, and less augmented modes receive higher frequency components. This avoids the requirement for pilots to switch response modes. An embodying control system can be produced by miming feedback control loops encoding the respective response modes in parallel, and multiplexing the command signaling to each response mode, filtering each copy of the command signaling respectively according the respective feedback control loop, and then combining the output of each feedback control loop to compute actuation demand.10-04-2012
20120253556REDUNDANT TWO STAGE ELECTRO-HYDRAULIC SERVO ACTUATOR CONTROL - A flight control system includes a dual stage actuator for moving a control surface. Each stage includes several control valves that are controlled independently to provide a desired redundancy. A flight controller generates a position command that is indicative of the position desired for the control surface. A first communication link is provided between several flight controllers to share information. Each of the flight controllers forwards the position command to actuator remote processing unit. The actuator remote processing unit receives position commands and generates a command signal that controls movement of the actuator using the control valves. Each of the actuator remote processing units is linked through a second communication link. Feedback and balancing of the different control valves is provided by the visibility accorded each actuator remote processing unit by the second communication link.10-04-2012
20080215194FORMULATION OF A PREVENTIVE MAINTENANCE MESSAGE RELATING TO THE FUNCTIONAL DEGRADATIONS OF AN AIRCRAFT - A method of preventive maintenance is disclosed for an aircraft. The aircraft includes components, including items of equipment of the aircraft and/or electronic modules and/or physical links. The lifetime information for the components is known. The aircraft also includes means for monitoring the components, a centralized maintenance system, and means for estimating the life time of the components. The aircraft carries out a set of functions, each being ensured by a chain of components. The method comprises several steps including, a first step of locating the degradations of the items of equipment, a second step making it possible to allocate the located degradations to the various functions of the aircraft, a third step of estimating the lifetime of the functions identified in the second step, and a fourth step of formulating the maintenance message constructed on the basis of the previous steps.09-04-2008
20080215192INTERACTIVE DEVICE FOR LEGACY COCKPIT ENVIRONMENTS - Disclosed is an aircraft computing and display device that includes a general purpose processor, a touch screen display and a housing. The processor executes logical instructions in the form of computer software. The touch screen display forms an interactive human-machine interface by displaying video graphics and accepting user input with a pressure sensitive surface. The housing retains the processor and the touch screen and is physically configured to replace a legacy device mounted in a cockpit instrument panel of the aircraft.09-04-2008
20110270469UNIVERSAL MOUNTING SYSTEM FOR A HANDHELD ELECTRONIC DEVICE - A universal mounting system for a handheld electronic device includes a handheld electronic device, a first mounting plate, and a second mounting plate. The handheld electronic device includes universal mounting members operable to mount to mounting plates. The first mounting plate includes first receiving members operable to detachably couple to the universal mounting members of the handheld electronic device. The first mounting plate also includes a fastener assembly operable to detachably couple the first mounting plate to a person. The second mounting plate includes second receiving members operable to detachably couple to the universal mounting members of the handheld electronic device. The second mounting plate also includes a connector assembly operable to attach the second mounting plate to a vehicle.11-03-2011
20130090786SYSTEMS AND METHODS FOR MANAGING CONTROLLER PILOT DATA LINK COMMUNICATION (CPDLC) SYSTEMS - Systems and methods for a non-integrated CPDLC solution are provided. In one embodiment, the system includes: a first and second computing system for respectively executing a first and second CPDLC application; a Human Machine Interface coupled to the first and second computing systems, the Human Machine Interface providing access to display screens generated by both the first and second CPDLC applications; and a data authority function that determines a data authority application from the first and second CPDLC applications based on which of the first and second CPDLC applications has a current data authority (CDA) session. The data authority function prevents the first CPDLC application from establishing a concurrent current data authority session when the second CPDLC application is the data authority application. The data authority function prevents the second CPDLC application from establishing a concurrent current data authority session when the first CPDLC application is the data authority application.04-11-2013
20130090787THREE-DIMENSIONAL DIGITAL MAP - Disclosed herein is a three-dimensional (3D) digital map system for implementing a navigation and ground collision preventing method using 3D terrain information. The 3D digital map system includes a terrain referenced navigation module configured to receive data from EGI (Embedded GPS/INS), a radio-altimeter (RALT) and a map database, corrects the data to perform accurate navigation computation, and outputs the corrected data, a collision avoidance warning module configured to generate a warning against collision of an aircraft with the ground or an obstacle using the corrected data, a 3D terrain database and an obstacle database, a terrain following module configured to generate a terrain following trajectory of the aircraft using the same information, and a Passive Ranging module configured to receive the 3D terrain database and line-of-sight (LOS) information of a target and calculate distance and position information of the target located on the ground.04-11-2013
20130124020AUTONOMOUS COLLISION AVOIDANCE SYSTEM FOR UNMANNED AERIAL VEHICLES - Autonomous collision avoidance systems for unmanned aerial vehicles are disclosed. Systems illustratively include a detect and track module, an inertial navigation system, and an auto avoidance module. The detect and track module senses a potential object of collision and generates a moving object track for the potential object of collision. The inertial navigation system provides information indicative of a position and a velocity of the unmanned aerial vehicle. The auto avoidance module receives the moving object track for the potential object of collision and the information indicative of the position and the velocity of the unmanned aerial vehicle. The auto avoidance module utilizes the information to generate a guidance maneuver that facilitates the unmanned aerial vehicle avoiding the potential object of collision.05-16-2013
20130124019AIRCRAFT CONTROL APPARATUS AND AIRCRAFT CONTROL SYSTEM - A plurality of control channels each include a power supply, an interface that receives a manipulation signal, an arithmetic processing portion that calculates and generates an operation command signal for actuators based on the manipulation signal, and a signal determination unit that determines a control signal for finally controlling the operation of the actuators and outputs the control signal. The arithmetic processing portions respectively provided in the plurality of control channels have designs different from one another. Each of the signal determination units determines the control signal by receiving a first operation command signal generated by the arithmetic processing portion of the control channel in which that signal determination unit is provided, and a second operation command signal generated in the arithmetic processing portion of another of the control channels, and comparing the first operation command signal and the second operation command signal, and outputs the control signal.05-16-2013
20130124015MULTI CORE VEHICLE MANAGEMENT SYSTEM AND METHOD - A flight management system (FMS) including a plurality of FMS components that can include a civil FMS component and a tactical FMS component. Each FMS component can have a processor programmed to execute an FMS software product. The FMS can also include a multi core FMS manager configured to control a plurality of flight management systems and coupled to the plurality of FMS components. The multi core FMS manager can include a plurality of FMS managers, each coupled to one of the FMS components, and a platform interface manager coupled to an avionics system. Each FMS manager can be adapted to transmit flight management data to, and to receive flight management data from, the FMS component to which it is coupled. The platform interface manager can be adapted to provide each FMS component access to the avionics system, such that an aircraft operator can control each FMS component via the FMS.05-16-2013
20130124016Derived Rate Monitor for Detection of Degradation of Fuel Control Servo Valves - A system for detecting degradation of a servo valve; having a controller, a servo valve, a position sensor, and a rate monitor. The controller receives inputs and transmits command data. The servo valve has an actuator and is conductively coupled to the controller to receive command data from the controller and move the actuator in response to the command data. The position sensor operably associated with the servo valve for measuring movement of the actuator and transmits corresponding movement data to the controller. The rate monitor coupled to the controller and position sensor for receiving the command data and the movement data as inputs respectively. The rate monitor processes the inputs to produce a steady state rate error signal. The rate monitor compares the steady state rate error signal to selected operational limits and produces a telemetry output when the operational limits are exceeded.05-16-2013
20130124017Control Panel System for a Vehicle - A method and apparatus for managing a programmable control panel for a vehicle. A number of first level control functions is assigned to the programmable control panel for the vehicle. A number of second level control functions is assigned to the programmable control panel based on a health of programmable control panels in the vehicle.05-16-2013
20080201026METHOD AND A DEVICE FOR CONTROLLING THE GROUND CLEARANCE OF AN AIRCRAFT - The present invention relates to a method and to a device for controlling and adjusting the ground clearance (h) of an aircraft (08-21-2008
20080201025Method of Distributing Braking Within at Least One Group of Brakes of an Aircraft - The invention provides a method of managing the braking of an aircraft having a plurality of brakes comprising friction elements, the method comprising the following steps for at least one group (08-21-2008
20110224846METHOD FOR ACTIVELY DEFORMING AN AERODYNAMIC PROFILE - The present invention relates to a method for actively deforming, by feedback control, an aerodynamic profile comprising an elastic material, applied to a part of the surface of the aerodynamic profile, said elastic material being in contact with a fluid flow; said elastic material being able to be deformed by one or more shape memory actuators placed in contact with the elastic material, said actuators being controlled by a computer connected to sensors. This method applies notably to a deformation of an aerofoil of a wing of an aircraft in flight, notably subsonic.09-15-2011
20100286848INTEGRATING AVIONICS FUNCTIONS - Systems, methods and computer program products for integrating one or more avionics functions are provided herein. In an embodiment avionics functions (e.g., ADS-B functions) are integrated by (1) receiving input from at least one avionics function module that executes at least one avionics function; (2) determining which of the avionics functions to allow to be engaged simultaneously, based on at different factors. In addition, embodiments select from different algorithms for the connected avionics functions.11-11-2010
20130184901VEHICLE ENERGY AND POWER MANAGEMENT METHOD AND SYSTEM - A method of managing energy and/or power in a vehicle, including: one or more vehicle power systems adapted to control one or more power consuming components of the vehicle and one or more power producing components of the vehicle; and one or more propulsive power systems adapted to control a propulsive power unit of the vehicle. The method includes: proposing a vehicle route for a predetermined mission and/or destination; determining a time-based operational plan for each of the vehicle power consuming components; determining the power required by the vehicle power consuming components and the propulsive power required by the vehicle; determining the power required from the vehicle power producing components and the propulsive power required by the propulsive power unit as a function of time during the operational plan; and varying the proposed vehicle route and/or the operational plan to optimize a predetermined performance criterion for the vehicle.07-18-2013
20130184900VEHICLE ENERGY CONTROL SYSTEM WITH A SINGLE INTERFACE - A system for controlling energy of a vehicle, for example an aircraft, characterized in that it comprises: 07-18-2013
20130184899METHOD FOR THE AUTOMATIC MONITORING OF AIR OPERATIONS NECESSITATING GUARANTEED NAVIGATION AND GUIDANCE PERFORMANCE - A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them.07-18-2013
20130151039METHOD FOR OPTIMIZING THE OVERALL ENERGY EFFICIENCY OF AN AIRCRAFT, AND MAIN POWER PACKAGE FOR IMPLEMENTING SAME - A method and system limiting specific consumption of an aircraft by matching sizing of a power supply to actual power needs of a cabin pressure control system. The method optimizes overall efficiency of energy supplied onboard an aircraft including, in an environment near the cabin, at least one main power-generating engine, sized to serve as a single pneumatic energy-generating source for the cabin and as an at most partial propulsive, hydraulic, and/or electric energy-generating source for the rest of the aircraft. The method minimizes power differential between a nominal point of the power sources when the sources are operating, and a sizing point of non-propulsive energy contributions of the sources when the main engine has failed, by equally dividing power contributions of the main engines and the main power generator under nominal operating conditions and in an event of failure of a main engine.06-13-2013
20130124018METHOD AND APPARATUS FOR USING ELECTRONIC FLIGHT BAG (EFB) TO ENABLE FLIGHT OPERATIONS QUALITY ASSURANCE (FOQA) - A method for using an Electronic Flight Bag (EFB) located on an aircraft to communicate Flight Operations Quality Assurance (FOQA) data to a remote aircraft flight data collection unit, is disclosed. The method may include receiving FOQA data from one or more aircraft systems while the aircraft is in-flight, and automatically transmitting the received FOQA data to a remote aircraft flight data collection unit for analysis.05-16-2013
20100292871ADAPTIVE SURVEILLANCE AND GUIDANCE SYSTEM FOR VEHICLE COLLISION AVOIDANCE AND INTERCEPTION - A surveillance and guidance method and system for use with autonomously guided, man-on-the-loop or man-in-the-loop guided vehicles where the presence of obstacles must be considered in guiding the vehicle towards a target includes a navigation system configured to determine the position of the vehicle on which it is equipped. A communication system is configured for data exchange between the vehicle, neighboring vehicles and ground stations. A surveillance system is configured to detect and locate fixed or moving targets and obstacles. A computer is configured to track the position of targets and obstacles and to provide guidance commands or 4D flight paths to perform collision avoidance with respect to traffic regulations and procedures, and operational airspace restrictions. Additional computer tasks include station keeping or interception of targets. A command and control system is configured to interact with a user interface and control the vehicle's actuators.11-18-2010
20100318245FLIGHT CONTROL SYSTEM - A flight control system for an aircraft includes a PCS generating a pilot control signal based on pilot operations of a stick control and others, an FCC for controlling flight control surfaces of the aircraft, a surface control device arranged for each flight control surface to control it based on a surface control signal transmitted from the FCC, and a data bus for connecting the FCC and the surface control device. The surface control device includes an ACE executing servo calculation process and outputting an actuator operation signal, and an actuator section for controlling hydraulic oil supplied to a hydraulic cylinder based on the actuator operation signal. A single flight control surface is controlled by a plurality of ACE and actuator section pairs, and the ACE includes a normal control section, a monitoring section, a backup control section, and the like.12-16-2010
20100318244Implementing Continuous Descent Approaches for Maximum Predictability in Aircraft - The present disclosure relates to methods of calculating and flying continuous descent approaches to an airport or the like, and to aircraft navigation systems for implementing these methods. The present disclosure resides in the recognition that greater predictability in arrival times may be achieved by flying continuous descent approaches by maintaining a constant aerodynamic flight path angle.12-16-2010
20100318243Method and Apparatus for Wireless Aircraft Communications and Power System Using Fuselage Stringers - A method and apparatus for transmitting wireless signals. An apparatus comprises a stringer having a channel and a waveguide located within the channel. The waveguide is capable of carrying a number of wireless signals.12-16-2010
20120283897Aircraft Task Management System - A method and apparatus for managing tasks in an aircraft. A current state of the aircraft is identified. A group of tasks is identified using a task database and the current state of the aircraft. The task database comprises the tasks for performance during different phases of flight of the aircraft by a flight crew and the group of tasks comprises different types of tasks from the tasks. The group of tasks is presented in a computer system.11-08-2012
20130158750Energy Management On Board an Aircraft - Energy management on board an aircraft includes: a plurality of thermal and electrical energy sources, a plurality of loads which are capable of being supplied with power by the various energy sources, among which at least one load is capable of being supplied with power by an electrical energy source and by a thermal energy source, and real-time management means for energy transfers from the various energy sources to the various loads as a function of the present and future energy requirement of the various loads and the present and future availability of the various sources, with the management means providing a permanent and standardized correlation between thermal and electrical energies.06-20-2013
20130158749METHODS, SYSTEMS, AND APPARATUSES FOR MEASURING FLUID VELOCITY - Methods, systems, and apparatuses are disclosed for a measuring the velocity of a fluid.06-20-2013
20110313599AIRCRAFT BACKUP CONTROL - A system is disclosed for controlling an aircraft when the hydraulic system of the aircraft has been compromised. The system includes a digital fly-by-wire control system configured to rescale at least one gain vector. The gain(s) may then used by a digital control to modulate engine thrust. In this manner, engine thrust modulation may be used for stabilization and control of control-configured aircraft without requiring a substantial change in piloting technique.12-22-2011
20110313598METHOD AND SYSTEM FOR DYNAMICALLY MANAGING A FLIGHT PROCEDURE OF AN AIRCRAFT FLIGHT PLAN - A method of managing a flight procedure of an aircraft flight plan, which has at least one segment, includes a step in which an additional attribute of the segment representative of a compulsory or optional nature of the flight of said segment is dynamically selected.12-22-2011
20110313597METHODS AND SYSTEMS FOR DISPLAYING ANNOTATIONS ON AN AIRCRAFT DISPLAY - Methods and systems are provided for presenting content on a display device onboard an aircraft. A method comprises displaying, on the display device, information corresponding to a first procedure and displaying an annotation associated with the first procedure on the display device. The first procedure is associated with an airport and prescribes operation of the aircraft in a vicinity of the airport, and the annotation comprises user-defined information pertaining to the first procedure.12-22-2011
20130190948AIRCRAFT RADIO SYSTEM - An aircraft radio system comprising a plurality of radios interconnected by a digital communications network, each radio having a transceiver and a dedicated processor platform, the aircraft radio system being configured to cause the dedicated processor platforms to constitute a virtual processing environment for the aircraft radio system. There is also an aircraft radio system comprising a plurality of discrete radios interconnected by a digital communications network, each radio having a transceiver, a dedicated processor platform and a server configured to support communications over the network using PPPoE, Point to Point Protocol over Ethernet, to provide a common digital interface between an aircraft domain and the radios for plural types of communication.07-25-2013
20130190949VEHICLE ENERGY CONTROL SYSTEM - A system for controlling energy of a vehicle, for example an aircraft, comprising a control interface able to be in at least one first and one second state, the first state being an instruction state in which the interface generates at least a first instruction for speed of variation of a current energy of the vehicle and the second state being a resting state in which it gives no instruction, the interface furthermore being configured to return into the second state after having been brought into the first state.07-25-2013
20130190950SYSTEM AND METHOD FOR PROVIDING AN AIRCRAFT NOISE ADVISORY DURING DEPARTURE AND ARRIVAL OF AN AIRCRAFT - A system and method for providing an aircraft noise advisory during departure and/or arrival of an aircraft are disclosed. In one embodiment, predefined allowable aircraft noise level information associated with a plurality of aircraft noise sensors located in the vicinity of airports are obtained. Further, predefined allowable aircraft noise level information associated with one or more of the plurality of aircraft noise sensors is presented on a display device in the aircraft, based on a current location of the aircraft, upon receiving noise data request from a pilot. Furthermore, current aircraft noise level information is obtained from one of the one or more aircraft noise sensors. In addition, the current aircraft noise level information is compared with predefined allowable aircraft noise level information associated with the one of the one or more aircraft noise sensors. Also, the aircraft noise advisory is displayed based on an outcome of the comparison.07-25-2013
20080300738METHOD OF OPTIMIZING A FLIGHT PLAN - A method of optimizing a flight plan of an aircraft used in a flight management system of an aircraft is disclosed. This method makes it possible to constrain the real cost index of the mission executed to the optimal cost index CI12-04-2008
20120029737CENTRALIZED NAVIGATION INFORMATION MANAGEMENT METHOD AND SYSTEM - In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display the inconsistency message on a first man-machine interface.02-02-2012
20120029736Method for Dynamically Consolidating Items of an Aeronautical Procedure - A method is provided for dynamically consolidating items of an aeronautical procedure in order to present to the operator the best action to perform according to the context of all the systems, in order to reduce his cognitive workload faced with an action to be carried out. The method consists, for each item of a procedure, in determining the text of the requested action, in choosing the text of the corresponding response that the crew must perform according to the general state and the configuration of the aircraft, in incorporating in the corresponding item the texts of the requested action and of the corresponding response, in displaying this duly enriched item, in detecting whether the requested action has indeed been accomplished and in displaying the result of this detection.02-02-2012
20120029735METHOD AND SYSTEM FOR VERTICAL NAVIGATION USING TIME-OF-ARRIVAL CONTROL - A method and systems for controlling an aircraft during descent are provided. The control system includes an input device configured to receive a speed margin for the vehicle and a processor communicatively coupled to the input device wherein the processor is programmed to automatically determine a flight path of the vehicle that is shallower than an idle flight path for the vehicle and generate a flight control surface control signal configured to maintain the determined flight path using the received speed margin. The control system further includes an output device communicatively coupled to the processor. The output device is configured to transmit the flight control surface control signal to a flight control system of the vehicle.02-02-2012
20130197721METHOD FOR DETECTING PERFORMANCE OF AN AIRCRAFT BASED ON A CUSTOMIZED MESSAGE - The present invention relates to a method for detecting the performance of the aircraft comprising: collecting data reflecting operation status of the aircraft; generating the customized message based on the collected data, wherein, the customized message is configured to include one or more main parameters related to the operation status of the aircraft; storing or transmitting the customized message; and detecting the performance of the aircraft based on the customized message.08-01-2013
20130197722MULTI-AXIS SERIALLY REDUNDANT, SINGLE CHANNEL, MULTI-PATH FLY-BY-WIRE FLIGHT CONTROL SYSTEM - A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers.08-01-2013
20130197723INTEGRATED APPROACH NAVIGATION SYSTEM, METHOD, AND COMPUTER PROGRAM PRODUCT - Systems, computer program products, and methods for displaying navigation performance based flight path deviation information during the final approach segment to a runway and during landing of non-precision flight modes are provided. Improved graphical depictions of navigation performance based flight path deviation information provide pilots and flight crew members with clear, concise displays of the dynamic relationship between ANP and RNP, mode and aspect of flight and related procedures, intersecting flight paths, and current actual flight path deviation from a predefined flight path during the final approach segment to a runway and during landing. For example, an enhanced IAN display may include NPS-type deviation scales to show RNP/ANP relationships and predetermined RNP markers to alert the pilots and flight crew members that the FMC has transitioned from an NPS display for RNAV (LNAV/VNAV) flight procedures to an enhanced IAN display for a non-precision (non-xLS) approach and/or landing.08-01-2013
20120035787LAYERED ARCHITECTURE FOR CUSTOMER PAYLOAD SYSTEMS - A layered architecture for customer payload systems is disclosed to provide a scalable, reconfigurable integration platform targeted at multiple unmanned aerial vehicles (UAV), and remove both UAV specific and payload equipment specific characteristics that increase complexity during integration. The layered architecture is a modular design architecture that is split by function. Standard interfaces are implemented between functional layers to increase reconfiguration possibilities and to allow reuse of existing components and layers without modification to the payload or UAV. The standard interfaces also promote easy connection and disconnection from other layer components. Additionally, once the layered architecture is implemented, technological or functional requirements changes can be isolated to one specific component layer, not the entire payload stack. As a result, payload designs based on the layered architecture reduces design time and cost, and allows for easier integration, operation, upgrades, maintenance, and repair.02-09-2012
20130204467Wind Calculation System Using a Constant Bank Angle Turn - A method and apparatus for operating an aircraft. The aircraft is flown at a constant bank angle in which the aircraft crosses an intended ground track for the aircraft. Information is identified about a wind using positions of the aircraft flying at the constant bank angle.08-08-2013
20130204468METHOD AND A DEVICE FOR PERFORMING A HEALTH CHECK OF A TURBINE ENGINE OF AN AIRCRAFT HAVING AT LEAST ONE SUCH ENGINE - A method of performing a health check of at least one turbine engine (08-08-2013
20130204469SYSTEM AND METHOD FOR REAL-TIME AIRCRAFT PERFORMANCE MONITORING - A computer apparatus and method to determine aircraft fuel mileage performance. The computer apparatus including a memory and a processor disposed in communication with the memory and configured to issue a plurality of instructions stored in the memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine the real-time fuel mileage performance for the aircraft based upon determined real-time aircraft mass data.08-08-2013
20120072058Pilotless Aircraft for Commercial and Military Use - An aircraft control system is described having an Automatic Monitoring System (“AMS”), an Aircraft Parameter Management Computer (“APC”), and a Flight Management Computer (“FMC”) to monitor the parameters of the aircraft automatically and to fly the aircraft without requiring a pilot to fly. The system respond to data within the systems and with data provided by a communication/navigation aid of the airport. The built-in systems of the aircraft process the data to allow pilotless operation of the aircraft along a predetermined route while maintaining proper spacing from prior art and other automated aircraft. An aircraft in accordance with the invention utilizes programmed software, electronics circuit and feedback system to fly the aircraft within the designated/destined routes and airports automatically while providing increased security by preventing accidents caused by incorrect or unauthorized human influence.03-22-2012
20120095622SYSTEMS AND METHODS FOR ENERGY CONSERVING WIRELESS SENSING WITH SITUATIONAL AWARENESS - A system and method is provided for monitoring aircraft health and status using a situation-aware sensing system. The system includes an independent power source, a sensor that continuously measures a signal of interest to yield sensor data, and a processor that compares the sensor data to threshold data. The processor adjusts an operational parameter of the situation-aware sensing system to conserve power when the sensor data does not exceed the threshold data. The processor further adjusts the operational parameter of the situation-aware sensing system to stop conserving power when the sensor data exceeds the threshold data.04-19-2012
20120095621TRAJECTORY TRACKING FLIGHT CONTROLLER - A six degree-of-freedom trajectory linearization controller (TLC) architecture (04-19-2012
20130211629DISPLAY SYSTEM - A display system for displaying a layout of controls in a simulator including at least one of an information display, a switch such as a toggle or push-button switch, and a monitoring device such as an indicator, or a gauge, for a vehicle, the display system including a touch sensitive screen which is generally transparent over a significant portion of its area, and a plurality of projectors which project onto a back of the screen, images of the vehicle controls, the projectors each being operatively connected to a computer controller which responds to the front of the screen being touched where a depicted control is displayed, to change the display in a manner to mimic the result of a corresponding actual vehicle control being operated.08-15-2013
20130211631Integrated Aircraft Flight Control Units - According to one embodiment, an integrated aircraft trim assembly features a shaft, a mechanical stop, a trim motor, a clutch, and a measurement device. The mechanical stop device is operable to at least partially prevent rotation of the shaft outside of an allowable range of motion. The trim motor has an output component in mechanical communication with the shaft. The clutch separates the trim motor from the shaft. The measurement device is proximate to the shaft and operable to measure a position of the shaft and communicate the measured position to a flight control computer operable to change a position of a flight control device.08-15-2013
20130211632Detection of aircraft descent anomaly - An aircraft ground or sea approach anomaly detection method. The method includes the steps of characterizing a flight phase of the aircraft, determining a prohibited flight envelope, defining a set of prohibited vertical speeds of the aircraft for given altitudes in relation to the ground or the sea, as a function of the flight phase of the aircraft characterized, and detecting a ground approach anomaly of the aircraft as a function of a current vertical speed and altitude in relation to the ground or the sea of the aircraft, in relation to the prohibited flight envelope determined.08-15-2013

Patent applications in class Aeronautical vehicle

Patent applications in all subclasses Aeronautical vehicle