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Altitude or attitude control or indication

Subclass of:

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

701001000 - VEHICLE CONTROL, GUIDANCE, OPERATION, OR INDICATION

701003000 - Aeronautical vehicle

Patent class list (only not empty are listed)

Deeper subclasses:

Class / Patent application numberDescriptionNumber of patent applications / Date published
701008000 Threshold or reference value 48
701011000 Auto pilot 30
701013000 Spacecraft or satellite 30
701007000 Air speed or velocity measurement 29
701005000 Rate of change (e.g., ascent, decent) 26
701010000 Compensation for environmental conditions 6
Entries
DocumentTitleDate
20100161158SYSTEMS AND METHODS FOR ENHANCING TERRAIN ELEVATION AWARENESS - A display system for an aircraft is provided. The display includes a processing unit configured to receive terrain data and navigation data and to supply display commands with symbology based on the terrain data and navigation data; and a display device coupled the processing unit and configured to receive the display commands and operable to render a three-dimensional view with the symbology. The symbology includes terrain, a zero pitch line, and elevation symbology indicating a relative elevation between the zero pitch line and a position in the view.06-24-2010
20080262664Synthetic vision system and methods - The present invention is directed to a system and methods, embodiments of which provide increased situation awareness information in an improved Synthetic Vision System (SVS). According to the present invention, a Primary Flight Display (PFD), a top-down view Multi-Function Display (MFD), and side-view Vertical Profile Display (VPD) are presented on one user interface with an input device, such as a transparent touch screen for quick and easy data entry. The present invention also provides color shading, such as red, to communicate areas where the aircraft may be in conflict with terrain or obstacles at a point in time in the future.10-23-2008
20090138143VIRTUAL CONTROL PANEL FOR AERONAUTICS ATTITUDE REFERENCE UNITS - The general field of the invention relates to devices for controlling the two attitude reference units of the AHRS type for aircraft, each AHRS comprising at least a first set of magnetometer measurements and at least a second set of gyroscopic measurements, each AHRS having two modes of operation, the first mode, called slave mode supplying the flight system with the information coming from the first set, the second mode, called DG mode supplying the flight system with the information coming from the second set. The device according to the invention comprises a display and means for displaying within this display a control window for these two attitude reference units, said window comprising three regions, the first region dedicated to the first AHRS unit, the second region dedicated to the second AHRS unit, the third region dedicated to the simultaneous control of the two AHRS units.05-28-2009
20100076624METHODS AND SYSTEMS FOR ACTIVE WING AND LIFT SURFACE CONTROL USING INTEGRATED AEROELASTICITY MEASUREMENTS - An active wing and lift surface control system for an aircraft is described. The wing and lift surface control system includes an aeroelasticity measurement system configured to provide at least one of real time wing twist measurements and real time measurements of aircraft body bending, at least one actuator mechanically coupled to a control surface of the aircraft, and a control system communicatively coupled to the aeroelasticity measurement system and to the at least one actuator. The control system is operable to receive the measurements from the aeroelasticity measurement system and generate control signals, based on the real time measurements, to operate the at least one actuator to adjust a drag associated with one or more of the wing and the aircraft body.03-25-2010
20090292408SYSTEM AND METHOD FOR COMMUNICATING INTENT OF AIRCRAFT - A method of an aircraft communicating a current position status, a current movement status, a current intent, and/or an intended future path, position, or intent of the aircraft may include the aircraft generating explicit first ownship information related to the current position status and/or the current movement status of the aircraft, and/or a flight management or other aircraft system of the aircraft generating information related to the intended future path, position, or intent of the aircraft. The aircraft may transmit the explicit first ownship information and/or the second information using an automatic dependent surveillance broadcast system transmitter. An airborne and/or ground receiver may receive the transmitted information related to the explicit first ownship information and/or the second information.11-26-2009
20120265373SYSTEMS AND METHODS FOR DIFFERENTIAL ALTITUDE ESTIMATION UTILIZING SPATIAL INTERPOLATION OF PRESSURE SENSOR DATA - Systems and methods for differential altitude estimation utilizing spatial interpolation of pressure sensor data are provided. In one embodiment, a method for mobile navigation comprises: measuring a horizontal location of a mobile navigation unit to generate two-dimensional horizontal coordinate data; measuring a barometric pressure at the mobile navigation unit with a sensor to obtain local pressure data; processing information representative of pressure data derived from a network of a plurality reference stations to obtain a correction factor; performing a calculation using the two-dimensional horizontal coordinate data, the local pressure data, and the correction factor to calculate an altitude coordinate; and determining an altitude of the mobile navigation unit from the altitude coordinate.10-18-2012
20090171517Shooshoo - According to a preferred embodiment of present invention, a method and apparatus for Computer Controlled tail-rotor anti-torque system, utilizing stored momentum of rotating body as well as power change (speed and torque) with changing pitch is provided.07-02-2009
20100042271METHOD AND DEVICE FOR MOVEABLE TAIL TRIMMING IN AN AIRCRAFT - The invention relates to a method for actuating an adjusting drive for adjusting an elevator (02-18-2010
20100042270ACTIVE PITCH CONTROL METHOD AND DEVICE FOR AN AIRCRAFT - The device (02-18-2010
20130060406Flight Control Laws for Vertical Flight Path - A flight control system and method for controlling the vertical flight path of an aircraft, the flight control system includes a stable decoupled model having a decoupled lateral equation of motion and a decoupled longitudinal equation of motion and a feedback command loop operably associated with the stable decoupled model. The feedback command loop includes a vertical flight path angle control law; an altitude control law; and a vertical speed control law.03-07-2013
20110282522GRAPHIC DISPLAY SYSTEM FOR ASSISTING VEHICLE OPERATORS - A system for converting audible air traffic control instructions for pilots operating from an air facility to textual format. The system may comprise a processor connected to a jack of the standard pilot headset and a separate portable display screen connected to the processor. The processor may have a language converting functionality which can recognize traffic control nomenclature and display messages accordingly. Displayed text may be limited to information intended for a specific aircraft. The display may show hazardous discrepancies between authorized altitudes and headings and actual altitudes and headings. The display may be capable of correction by the user, and may utilize Global Positioning System (GPS) to obtain appropriate corrections. The system may date and time stamp communications and hold the same in memory. The system may have computer style user functions such as scrollability and operating prompts.11-17-2011
20110295449METHODS AND SYSTEMS FOR REDUCING ANGULAR VELOCITY USING A GYROSCOPE ARRAY - Methods and systems are provided for reducing angular velocity of a vehicle using a gyroscope array. A method comprises dithering a gyroscope of the gyroscope array, obtaining current through a gimbal motor of the gyroscope while dithering the gyroscope, determining a gimbal rate command to reduce angular velocity of the vehicle based on the current through the gimbal motor obtained while dithering the gyroscope, and operating the gimbal motor of the gyroscope based on the gimbal rate command.12-01-2011
20100076625FLIGHT CONTROL COCKPIT MODES IN DUCTED FAN VTOL VEHICLES - A flight control system for aircraft, such as for a vehicle with a ducted fan propulsion system which also produces rotary moments and side forces for control purposes. The flight control system of the present invention is designed in a manner that will ensure the safety of the vehicle in event of a malfunction in any one of its channels and enable the flight to continue down to a safe landing.03-25-2010
20080208400Method and System for Assisting Flight Control of a Low-Flying Aircraft - The system (08-28-2008
20110172854System and method for effecting vehicle maneuver to compensate for IMU error - The effects of IMU gyro and accelerometer bias errors are significantly reduced in accordance with the present teachings by a system or method for commanding an IMU or vehicle through a series of preprogrammed maneuvers. The maneuvers can be designed to minimize the effects of other gyro errors including scale factor errors, nonlinearities, cross coupling/misalignment, and scale factor asymmetries. A sample maneuver is provided which demonstrates performance based on a sequence of roll and yaw maneuvers resulting in zero build up of error at the end of a maneuver cycle period as a result of these errors. Modification of the system involves the addition of control logic to determine the maneuver period, maneuver rate, and vehicle orientation. No additional hardware beyond possible fuel required to perform the maneuver is required.07-14-2011
20110270472Distance Separation Criteria Indicator - Methods, systems, and computer-readable media described herein provide for the display of aircraft traffic and climb/descent information on an aircraft display. Flight data is received from a traffic aircraft in the vicinity of an ownship aircraft. Similar flight data is determined for the ownship aircraft. The flight data for the traffic aircraft and the ownship aircraft is used to determine a criteria indicator that is associated with at least the longitudinal separation and closure rate between the two aircraft. According to various embodiments, a number of altitude indication lines are displayed and an aircraft traffic indicator and ownship indicator corresponding with the traffic aircraft and ownship aircraft are displayed on the appropriate altitude indication lines. The criteria indicator is displayed so that the position of the criteria indicator with respect to the aircraft traffic indicator and ownship indicator informs a pilot as to whether an altitude change is possible.11-03-2011
20090319100SYSTEMS AND METHODS FOR DEFINING AND RENDERING A TRAJECTORY - Embodiments of systems and methods for defining and rendering a trajectory of an aircraft include a processing system that causes a three dimensional trajectory depiction to be rendered on a display device. The trajectory depiction includes at least one trajectory element indicator that corresponds to at least one trajectory element of a flight plan. The processing system also receives one or more user interface commands that indicate selection by a user of a selected trajectory element indicator and user-initiated movement of the selected trajectory element indicator from a first display position to a second display position. The processing system determines one or more modified characteristics of a trajectory element corresponding to the selected trajectory element indicator in response to the user-initiated movement, and causes a modified trajectory depiction to be rendered. The modified trajectory depiction includes the selected trajectory element indicator rendered at the second display position.12-24-2009
20080269963Systems and Methods for Estimating Position, Attitude, and/or Heading of a Vehicle - A system for estimating at least one of position, attitude, and heading of a vehicle is disclosed. The system includes at least three gyroscopes configured to output a signal indicative of inertial angular rates around three mutually orthogonal axes of the vehicle and at least three accelerometers configured to output a signal indicative of accelerations along three mutually orthogonal axes of the vehicle. The system further includes a triaxial magnetometer configured to output a signal indicative of a projection of ambient magnetic field on three mutually orthogonal axes of the vehicle. The system also includes a sensor configured to output a signal indicative of vehicle altitude and a differential pressure sensor configured to output a signal indicative of airspeed of the vehicle. The system further includes a device configured to receive the signals and estimate at least of one of position, attitude, and heading of the vehicle.10-30-2008
20090157238DEVICE FOR SAFELY OPERATING A FLIGHT CONTROL ACTUATOR OF AN AIRCRAFT - The field of the invention is that of safe devices for operating the actuators of aircraft and more specifically the flight control actuators of a helicopter. The invention consists of a safe control device for commanding an actuator (06-18-2009
20090138142Motion-resolving hover display - An integrated flight instrument which provides unambiguous information regarding the motion of a hovering aircraft. The instrument accurately depicts motion in six degrees of freedom (roll, pitch, yaw, forward translation, lateral translation, and vertical translation), as well as aircraft power requirements and utilization.05-28-2009
20090177340VERTICAL TAKEOFF AND LANDING AIRCRAFT - A vertical takeoff and landing aircraft according to the invention includes multiple thrust producing devices that produce thrusts applied in the substantially vertically upward direction; a target attitude setting portion that sets a target attitude used in attitude control of the aircraft; an inertia moment deriving portion that derives an inertia moment applied around a predetermined rotational axis of the aircraft; and a thrust adjustment portion that adjusts, during the attitude control of the aircraft, the thrusts to be produced by the respective thrust producing devices based on the target attitude set by the target attitude setting portion and the inertia moment during the attitude control, which is derived by the inertia moment deriving portion.07-09-2009
20090326742METHODS AND APPARATUS FOR VERTICAL MOTION DETECTOR IN AIR TRAFFIC CONTROL - Methods and apparatus for vertical motion detection of objects, such as aircraft. In one embodiment, a method comprises receiving altitude data for an object, determining a residual of a lag function, wherein the lag function comprises a moving average of the altitude data for the object, and wherein the residual corresponds to a difference between a value for the lag function and the object altitude data at a given time such that the residual grows in magnitude over time in response to the object transitioning from level flight to vertical motion, detecting vertical motion of the object by comparing a sum of data derived from the residuals against a threshold value, and outputting a vertical motion indicator after detecting the vertical motion of the object.12-31-2009
20090326741DEVICE AND METHOD FOR EXTRACTING TERRAIN ALTITUDES - The present invention relates to a method and a device for extracting terrain altitudes notably for a display of a sectional view of a terrain overflown by an aircraft. The device for extracting terrain altitudes along a trajectory (12-31-2009
20110224848APPARATUSES 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.09-15-2011
20090024259Stores dependent angle of attack feedback - A method for adjusting angle of attack feedback gain based characteristics and position of mounted stores, and a control system using the method.01-22-2009
20110224847SYSTEM AND METHOD FOR RENDERING AN ONBOARD AIRCRAFT DISPLAY FOR USE WITH IN-TRAIL PROCEDURES - A system and method for displaying aircraft traffic information on an onboard display element of a host aircraft are provided. The system obtains current flight status data of the host aircraft and current flight status data of a second aircraft that is near the host aircraft, and processes the current flight status data of the host aircraft and the current flight status data of the second aircraft to determine an in-trail procedure (ITP) opportunity region for the host aircraft. The ITP opportunity region is associated with conditions that satisfy ITP criteria for the host aircraft. The system renders, on the onboard display element, an ITP display comprising graphical representations of the host aircraft and the second aircraft positioned in accordance with the current flight status data of the host aircraft and the current flight status data of the second aircraft. The ITP display further includes a graphical representation of the ITP opportunity region.09-15-2011
20100274419Method and Device for Adjusting the Trajectory of an Aircraft in a Climb Circuit - A method of adjusting the trajectory of an aircraft flying a climb circuit, of substantially helical form corresponding to a succession of racetracks, denoted HOLD, the last HOLD, called the exit HOLD, having predefined geometric characteristics and comprising a lock-on point, allowing the aircraft to enter and to exit in the HOLD, the aircraft attaining the setpoint altitude of the climb circuit during the flight of the exit HOLD, comprises at least three steps, including: a step of computing the prediction of the position of the aircraft when the setpoint altitude will be attained; a step of computing the remaining distance to be traveled, between the position of the aircraft when the setpoint altitude will be attained and the lock-on point; and a step making it possible to carry out an adaptation of the form of the exit HOLD so as to minimize the remaining distance to be traveled DELTA.10-28-2010
20100152929SYSTEMS AND METHODS OF REDUNDANCY FOR AIRCRAFT INERTIAL SIGNAL DATA - An aircraft inertial system comprises at least two inertial reference units (IRU) that provide a first set of inertial signal data for an aircraft and at least two attitude heading reference systems (AHRS) that provide a second set of the inertial signal data for the aircraft. At least one primary flight display receives the first and the second sets of the inertial signal data, and a standby flight display receives at least the second set of the inertial signal data from at least one of the AHRS. When a single fault condition occurs, the primary flight display continues to operate with fail-operational redundancy from at least three independent sources of the inertial signal data comprising one or more IRU and AHRS combinations. The standby flight display will operate using a different source of the inertial signal data than the source of the inertial signal data for the primary flight display.06-17-2010
20100185344SURFACE CONTROL SYSTEM - A method, apparatus, and computer program product are present for controlling a control surface. A load is identified on the control surface to form an identified load. A direction of movement of the control surface is identified from the identified load to form an identified movement. A brake associated with the control surface is engaged if the identified movement is away from a desired position for the control surface.07-22-2010
20100161159AUTOMATIC STRATEGIC OFFSET FUNCTION - A system may generate a modified flight plan for an aircraft based on an original flight plan. The system may provide an automatic strategic offset function that includes an autoflight system; a sensor system including at least one of a global positioning system, an inertial reference unit, or an air data computer; and a flight management computer. The flight management computer may be operably coupled with the autoflight system and/or the sensor system. The flight management computer may process a flight plan of the vehicle and generate a non-uniform offset value in the vertical and/or lateral orientation between the flight plan and a boundary. The offset value may be used to create an offset flight plan for navigating an aircraft.06-24-2010
20090076669METHODS AND SYSTEMS FOR CONTROLLING MULTI-BODY VEHICLES WITH FUEL SLOSH - Methods and systems for controlling multi-body vehicles with fuel slosh are provided. In a method for stabilizing a vehicle with fuel slosh, a controller for a multi-body assembly is formed by selecting vehicle configuration and velocity as states of a rigid body. Equations of motion are written for the multi-body assembly, and velocity states are determined that are unactuated. A decoupling transformation is defined from the unactuated velocity states. The equations of motion are transformed using the decoupling transformation such that unactuated states are decoupled from actuated states. A slosh state estimator is coupled to the controller such that it is in operative communication with an input to the controller and an output from the controller.03-19-2009
20100241293TUNABLE ARCHITECTURE FOR AIRCRAFT FAULT DETECTION - A method for detecting faults in an aircraft is disclosed. The method involves predicting at least one state of the aircraft and tuning at least one threshold value to tightly upper bound the size of a mismatch between the at least one predicted state and a corresponding actual state of the non-faulted aircraft. If the mismatch between the at least one predicted state and the corresponding actual state is greater than or equal to the at least one threshold value, the method indicates that at least one fault has been detected.09-23-2010
20100222943FLIGHT CONTROL SYSTEM AND AIRCRAFT COMPRISING IT - The flight control system comprises: 09-02-2010
20110130895METHOD OF OBTAINING A LOCAL TERRAIN ELEVATION DATABASE FROM DETECTOR MEANS ON BOARD A VEHICLE - A method essentially comprising a step of storing each plot mesh. Each plot mesh receiving plots sent thereto by detector means and retaining in memory at least the altitude of the highest plot and the number of plots neighboring said highest plot in said mesh. The altitude and the number of plots neighboring are updated each time a new plot is sent to the plot mesh. A step of rejecting plot meshes is presenting a number of neighboring plots that is less than a predetermined rejection threshold value. The rejection threshold value is a function of the position of the mesh relative to the detector means. A step is preparing the local terrain elevation database from the plot meshes (M(i,j)) that are not rejected.06-02-2011
20110029160METHODS AND APPARATUS FOR A TANDEM DIVERT AND ATTITUDE CONTROL SYSTEM - An aeronautical vehicle includes at least one set of tandem divert thrusters incorporated into the body. Each set of tandem divert thrusters includes a first divert thruster and a second divert thruster, each configured to provide substantially equal thrust forces at substantially the same time and in substantially opposite directions such that the moment reference point lies between the first and second divert thrusters.02-03-2011
20110029161VISUAL AUTOPILOT FOR NEAR-OBSTACLE FLIGHT - This present invention describes a novel vision-based control strategy for autonomous cruise flight in possibly cluttered environments such as—but not limited to—cities, forests, valleys, or mountains. The present invention is to provide an autopilot that relies exclusively on visual and gyroscopic information, with no requirement for explicit state estimation nor additional stabilisation mechanisms.02-03-2011
20110046823PROCESS AND DEVICE FOR OPTIMISING THE PERFORMANCE OF AN AIRCRAFT IN THE PRESENCE OF A LATERAL DISSYMETRY - A process and device for optimising the performance of an aircraft in the presence of a lateral dissymmetry is disclosed. The device (02-24-2011
20110082604SYSTEM AND METHOD FOR DIVERT AND ATTITUDE CONTROL IN FLIGHT VEHICLES - A system and method is provided for thruster control in a flight vehicle. The system and method uses a proportional derivative matrix control technique to determine thrust commands in a Divert and Attitude control (DAC) system. The proportional derivative matrix control system is configured to receive pitch, roll and yaw commands as inputs, and generate thrust commands as outputs. The performance of the proportional derivative matrix controller is such that the thrust commands can achieve the desired attitude angles quickly and with reduced fuel consumption. The matrix control system can efficiently control a variety of thrusters, including asymmetric thrusters having different moment arms. The matrix control system is particularly suitable to the control of DAC systems with asymmetric thrusters that are configured for attitude control.04-07-2011
20100299003REAL-TIME COMPENSATION OF INERTIAL SENSOR BIAS ERRORS UNDER HIGH SPIN RATE CONDITIONS - A method of estimating bias errors for an air vehicle in flight under high spin conditions is provided. The method comprises collecting a first set of data samples at a first time and collecting a second set of data samples at a second time. The first time and the second time occur after deployment of the air vehicle and before canard shock. The first and second sets of data samples comprise roll rate data from at least a first gyroscope and acceleration data from at least a first accelerometer. At least a first estimated accelerometer bias from the first and second sets of data samples is calculated.11-25-2010
20100305783ENHANCED VERTICAL SITUATION DISPLAY - A vertical situation display system for use in a vehicle such as, for example, an aircraft, is provided. A side view of an intended route of flight may be shown with altitude restrictions, airspace and instrument approach information, a projected flight path and range to airspeed symbol. The system may show terrain, weather, and traffic information along the intended route of flight. The system may be used in conjunction with a navigational display to enhance situational awareness. The system includes a computer, an electronic display device, an electronic entry device, a memory and a database. The database may contain terrain, airspace and flight planning data and may be updatable.12-02-2010
20100070113DEVICE FOR SERVOING GRAPHIC REPRESENTATIONS OF THE AIR ENVIRONMENT - Device for servoing graphical representations of the aerial environment for aircraft, an avionics the device including a display, a computer and memory in communication with the computer, the memory storing means for generating images of environmental data, said data being servoed by the first calculation resource and periodically refreshed in a first time interval. The device comprises a calculation resource providing an angle of heading of the aircraft relative to North and its geo-referenced current position, these data being servoed, periodically, in real time in a second time interval. The representation of a part of the environmental data on the viewing screen of the device is servoed and refreshed during the second time interval and positioned and oriented graphically, by the display, according to the last current angle of the position of the aircraft calculated and of the last geo-referenced current position.03-18-2010
20110054719METHOD FOR DRAMATICALLY REDUCING THE TAKE-OFF RUN OF AN AIRCRAFT - According to the invention, during take-off, the aircraft (AC) is given an attitude (θ03-03-2011
20110046824Device for piloting a vehicle and method for the motorised assistance and control of such a piloting device - The invention relates to a piloting device comprising a piloting component (02-24-2011
20110137498UNMANNED AIRCRAFT AND AERIAL SURVEILLANCE SYSTEM FOR UNMANNED AIRCRAFT - An unmanned aircraft includes a camera, a laser ranging system and a driving unit. The laser ranging system measures a distance to an object in the field of view of the camera. The driving unit rotates the field of view. Thus, it is possible to acquire relative position data of the object around the unmanned aircraft with a small and light-weight unit.06-09-2011
20100185345METHOD OF ESTIMATING AN ANGLE OF ATTACK AND AN ANGLE OF SIDESLIP OF AN AIRCRAFT - A method for estimating an angle of attack and an angle of sideslip of an aircraft has a plurality of control surfaces each adjustable with respect to an associated reference surface. The method includes measuring quantities representative of the angle formed by each control surface with respect to the associated reference surface; measuring the effective rolling speed, the effective pitching speed, and effective yawing speed of the aircraft. A linearized model of a state observer is defined according to the following equations:07-22-2010
20110166722ALTITUDE MEASUREMENT APPARATUS AND METHOD - Provided is an altitude measurement apparatus and method that may measure an altitude of an aircraft without using a separate altimeter. The altitude measurement apparatus may include a camera unit being provided to a vertical takeoff and landing (VTOL) aircraft to collect an image of a circular mark formed on the ground, and a calculation unit to calculate an altitude of the VTOL aircraft based on the collected image. Accordingly, the altitude measurement apparatus may measure the altitude using a simple structure such as the circular mark formed on the ground, and be configured at inexpensive costs.07-07-2011
20120022723Method And Device For Determining And Updating A Target Altitude For An Emergency Descent Of An Aircraft - Method and device for determining and updating a target altitude for an emergency descent of an aircraft01-26-2012
20120158219TRAJECTORY BASED SENSE AND AVOID - A trajectory-based sense-and-avoid system for use on an aircraft is provided that utilizes 4-D constructs, such as 4-D trajectories or 4-D polytopes, to maintain separation from other aircraft and/or to avoid collisions with other aircraft. In certain embodiments the trajectory-based sense-and-avoid system utilizes 4-D trajectories provided from an external source and/or 4-D trajectories estimated based on a variety of data sources during operation.06-21-2012
20100250029DIGITAL SMART SERVO CONTROLLER FOR SAFETY CRITICAL VEHICLE CONTROL - A smart servo controller that is operable to control a redundant configuration of servo motors corresponding to mechanical control surfaces of an aerial vehicle is described. The controller (i) outputs the necessary electrical signals that control the servo motors corresponding to each control surface, (ii) monitors those signals, (iii) monitors the positions of the servo motor shafts, and (iv) provides notification to a flight control computer upon detecting a servo malfunction.09-30-2010
20100204852PROGNOSTIC AND HEALTH MANAGEMENT ACCURACY MAINTENANCE SYSTEM AND METHOD - A prognostic and health accuracy maintenance system and method for a system following on-site replacement of a component in the system is provided. A system characterization model of at least portions of the system is generated and embedded within a controller in the system. The system characterization model is adapted to receive a plurality of signals that are each representative of an operational parameter within the system and is responsive to each of the signals to generate simulation response data and determine system health based, at least in part, on the simulation response data. When a component within the system is replaced, a determination is made as to whether the replacement component exhibits one or more operational performance characteristics that differ from the component it replaced. If so, the embedded system characterization model is updated in-situ.08-12-2010
20120173053Flight Control System For Flying Object - A flight control system for a flying object comprises a flying object, a navigating means provided in the flying object, a position measuring unit 07-05-2012
20100036548METHOD AND SYSTEM FOR OPERATING A DISPLAY DEVICE ON-BOARD AN AIRCRAFT - Methods and systems for operating a display device that is viewable by a user of an aircraft are provided. A first image is caused to be displayed on the display device. The first image is at least representative of a field of view from on-board the aircraft of an actual terrain. A second image is rendered over the first image on the display device. The second image includes a vertical position indicator indicating a vertical position of the aircraft relative to a selected flight path. The vertical position indicator is moved in a pitch direction on the display device in response to the aircraft moving relative to the actual terrain. The pitch direction corresponds to a change in the pitch of the aircraft.02-11-2010
20120253562Method And Device For Automatically Managing The Vertical Profile Of The Flight Plan Of An Aircraft - The device includes means for determining a plurality of successive standard flight sections (S10-04-2012
20120226395METHOD AND SYSTEM FOR DETERMINING THE ATTITUDE OF AN AIRCRAFT BY MULTI-AXIS ACCELEROMETRIC MEASUREMENTS - An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes.09-06-2012
20100204853FLIGHT CONTROL SYSTEM AND AIRCRAFT COMPRISING IT - The flight control system comprises: 08-12-2010
20100185346AERIAL PAYLOAD DEPLOYMENT METHOD - The present invention provides a method, comprising: providing an aerial platform having an outer shell; disposing a gas containment system within the outer shell; attaching the aerial platform to an object using a tether system; and inflating the aerial platform and lifting a payload; wherein the aerial platform is configured such that it may be completely collapsed when deployed.07-22-2010
20130024052SYSTEMS AND METHODS FOR GENERATING A COMMAND TRAJECTORY - A system for use in generating a command trajectory for an aircraft is provided. The system includes a natural frequency determining module configured to determine a closure rate of the aircraft to a selected flight path, compare the closure rate of the aircraft to a threshold closure rate, and calculate a natural frequency based on whether the closure rate is below the threshold closure rate. The system further includes a command processor coupled to the natural frequency determining module and configured to receive the calculated natural frequency from the natural frequency determining module, and generate a command trajectory using the calculated natural frequency.01-24-2013
20130179010SYSTEM AND METHOD FOR INDICATING A PERSPECTIVE COCKPIT FIELD-OF-VIEW ON A VERTICAL SITUATION DISPLAY - An aircraft display system is provided and configured to render a cockpit display having a field-of-view. The system comprises a monitor and a processor coupled to the monitor and configured to generate a vertical situation display on the monitor. The vertical situation display includes at least one graphic indicative of a region of the terrain encompassed by the field-of-view.07-11-2013
20090088911METHOD AND SYSTEM FOR MANEUVERING AN AIRCRAFT BY SHIFTING ITS CENTER OF GRAVITY - A method to maneuver an aircraft in flight, in which the center of gravity of the aircraft is shifted by transferring fuel from at least one first fuel tank to at least one second fuel tank of the aircraft. A system implementing this method, the system including: at least one first fuel tank and at least one second fuel tank, a flight control unit capable of sending out a maneuver command upon being handled. A computer capable, as a function of this command, of determining a quantity of fuel to be transferred from the first tank to the second tank, at least one means of transfer connecting the first and second tanks and being controlled by the computer, to transfer the fuel from the first tank to the second tank04-02-2009
20080208399ELECTRONIC FLIGHT BAG SYSTEM AND METHOD - An electronic flight bag (EFB) system for use on a mobile platform, for example, a commercial or military aircraft. The EFB system includes first and second independent processors that run first and second independent software applications. The first software application may be a Type C application requiring a high level of governmental agency certification for use on an aircraft while the second application may be a commercially available, off-the-shelf software application that requires no certification. The two processors share a common display, although the first processor is provided with control over the display so that use of the display by the second processor can be inhibited or limited by the first processor as may be needed to display more critical flight or aircraft related information. The first processor is also provided with control over a switching subsystem that can interrupt the flow of information from external I/O devices to and from the second processor, if needed.08-28-2008
20100286849Systems and Methods for Controlling Aircraft Flaps and Spoilers - Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned at least partially aft of the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.11-11-2010
20130151040LOW-ALTITUDE ALTIMETER AND METHOD - A low-altitude altimeter (06-13-2013
20090187292INTEGRATED PITCH, ROLL, AND YAW INCEPTOR - A method and apparatus for a control system for an aircraft. The control system comprises a grip, a set of feedback components connected to the grip, and a set of sensors. The set of feedback components transmit a restoring force opposite to a movement of the grip. The set of sensors are capable of detecting pitch input, roll input, and yaw input in response to the movement of the grip.07-23-2009
20130090788FLIGHT CONTROL LAWS FOR FULL ENVELOPE BANKED TURNS - A flight control system and method for controlling full envelope banked turns of an aircraft, the flight control system including one or more of a control law architectures having one or more control laws adapted for controlling the flight of an aircraft for full envelope banked turns.04-11-2013
20130190951PRESSURE ALTITUDE STABILIZATION - A method and apparatus is provided for determining the altitude of an aircraft. In accordance with the method, Global Positioning Satellite (GPS) data is received from a plurality of GPS satellites and a GPS altitude value is determined from the GPS data. In addition, a pressure altitude value is determined. An altitude difference is determined between the GPS altitude value and the pressure altitude value. At least one of the GPS altitude value and the pressure altitude value is adjusted using the altitude difference.07-25-2013
20120095623DEVICE FOR ASSISTING AIRCRAFT CREW WHEN PERFORMING FLIGHT LEVEL CHANGES - This device providing assistance to aircraft crew for a flight level change of the aircraft in air traffic, comprising means for viewing the position of the aircraft in the vertical plane, is wherein the viewing means comprise: display means capable of displaying an image comprising at least one zone corresponding to a target altitude (FL) for the aircraft, and in that it comprises: selection means for selecting said zone in the image.04-19-2012

Patent applications in class Altitude or attitude control or indication

Patent applications in all subclasses Altitude or attitude control or indication