| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 701005000 | Rate of change (e.g., ascent, decent) | 25 |
| 20110202207 | Method And Device For Automatically Protecting An Aircraft Against An Excessive Descent Rate - The device ( | 08-18-2011 |
| 20100076627 | APPARATUSES 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. | 03-25-2010 |
| 20100076626 | METHOD AND DEVICE FOR PREVENTING USELESS ALARMS GENERATED BY AN ANTI-COLLISION SYSTEM ON BOARD AN AIRPLANE - The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax). | 03-25-2010 |
| 20090043431 | METHOD AND APPARATUS FOR MINIMIZING THE NOISE EMITTED BY A ROTORCRAFT DURING TAKE-OFF AND LANDING - The method includes a preliminary period in which a reference rotorcraft is used that corresponds to a rotorcraft of a particular type, with a series of noise measurements being performed on said rotorcraft ( | 02-12-2009 |
| 20110208374 | METHODS AND SYSTEMS FOR DISPLAYING PREDICTED DOWNPATH PARAMETERS IN A VERTICAL PROFILE DISPLAY - Methods and systems are provided for presenting operating information for an aircraft in a vertical profile displayed on a display device associated with the aircraft. The vertical profile graphically depicts at least a portion of a flight plan for the aircraft, wherein the portion of the flight plan comprises a plurality of reference points. The method comprises calculating, for each reference point of the plurality of reference points, a predicted value of a first operating parameter for the aircraft at the respective reference point based at least in part on current status information for the aircraft, resulting in predicted values for the first operating parameter, and displaying the predicted values for the first operating parameter in the vertical profile. | 08-25-2011 |
| 20080234880 | METHOD AND DEVICE FOR LIMITING THE ROLL COMMAND OF AN AIRCRAFT AS A FUNCTION OF A THRUST ASYMMETRY - The device ( | 09-25-2008 |
| 20090030566 | Navigating UAVs In Formation - Navigating UAVs in formation, including assigning pattern positions to each of a multiplicity of UAVs flying together in a pattern; identifying a waypoint for each UAV in dependence upon the UAV's pattern position; piloting the UAVs in the pattern toward their waypoints in dependence upon a navigation algorithm, where the navigation algorithm includes repeatedly comparing the UAV's intended position and the UAV's actual position and calculating a corrective flight vector when the distance between the UAV's actual and intended positions exceeds an error threshold. The actual position of the UAV may be taken from a GPS receiver on board the UAV. | 01-29-2009 |
| 20090138144 | VERTICAL PATH CONTROL AUGMENTATION USING LATERAL CONTROL SURFACES - In one embodiment of a method for reducing vertical position errors of an aircraft, the displacement of the aircraft from a commanded vertical path may be determined. A determination may be made as to whether a magnitude of a vertical path error meets criteria. No more steps of the method may be followed if the vertical path error does not meet the criteria, while the vertical path error may be converted into a delta lift command if the vertical path error meets the criteria. The delta lift command may be limited. The delta lift command may be converted into lateral surface position commands for control surfaces. The lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the lateral surface position commands. | 05-28-2009 |
| 20090055035 | METHOD FOR POSITIONING ORDERS WITH DELAYED EXECUTION IN AN AIRCRAFT FLIGHT PATH - The invention relates to a navigation aid method of an aircraft comprising a step for positioning an execution order in a flight plan then in a flight path. When the order is for deferred execution, that is, comprises a condition, estimating the position of the aircraft when the condition associated with the order is satisfied, modifying the flight plan based on the estimated position according to the order, computing a new flight path based on the flight plan. | 02-26-2009 |
| 20090326743 | AUTOMATED THROTTLE CONTROL SYSTEM - A throttle control system that is compensated for mountain wave conditions includes an auto throttle computer and a detector for detecting the pitch or pitch angle of the aircraft. The computer is used for determining the rate of change of pitch i.e. the first derivative of pitch angle and the rate of change of the rate of change of pitch i.e. the second derivative for generating a signal indicative of the rate of change of the rate of change of pitch. The signal from the auto throttle computer is combined with the signal from the signal indicative of the second derivative to produce a combined signal which is fed to a servo assemble and motor for adjusting the throttle of an aircraft. | 12-31-2009 |
| 20100168936 | Method of Constructing a Vertical Profile in the Event of Depressurization in an Area with Risks and Associated Devices - The method of generating a secure flight plan portion in the event of depressurization corresponding to a time-conditioned descent profile that may include a succession of levels, comprises:
| 07-01-2010 |
| 20080215195 | Terrain Avoidance Method and System For an Aircraft - The invention concerns a terrain avoidance method and system for an aircraft. The system comprises a collision alarm device ( | 09-04-2008 |
| 20090287365 | CONVERTER FOR CONVERTING A LOAD FACTOR COMMAND INTO A LONGITUDINAL ATTITUDE DEVIATION INSTRUCTION - The invention relates to flight control systems for aircraft, which have large control loops delivering load factor commands and which are applied to flight controls more suited to the following by the pilot of a longitudinal attitude deviation instruction than to the following of a load factor instructions. It consists of a small control loop generating a deviation indicator displayed by the flight director on the PFD screen, with a converter for converting a controlled load factor into a longitudinal attitude deviation instruction comprising a bandpass filter allowing the integration for the calculation of the longitudinal attitude deviation instruction value in the piloting frequency span only. | 11-19-2009 |
| 20100010693 | METHOD AND A CALCULATING UNIT FOR CALCULATION OF A RECOVERY FLIGHT PATH - The invention relates to a method for calculating a flight path avoiding a collision with the ground when an aircraft dives towards the ground. The method includes receiving signals including information of a dive angle of the aircraft in relation to the imaginary ground plane, and a present roll angle of the aircraft, and calculating a flight path that avoids collision with the ground on the basis of the information. The calculation includes calculating a need for rolling the aircraft based on the present roll angle, and calculating a need for changing the direction of the velocity vector of the aircraft so that the change has a component in an upward direction in relation to the reference frame of the aircraft. The calculation of the need for rolling the aircraft is also based on the dive angle so that the calculated flight path turns sideways when the dive angle surpasses a specified dive angle and when the present roll angle is larger than zero degrees, and so that the flight path continues in a forward direction when the dive angle is below the specified dive angle. The invention also relates to a ground collision calculating unit, a computer program, and a computer readable medium. | 01-14-2010 |
| 20080215196 | METHOD AND SYSTEM USED BY AN AIRCRAFT TO FOLLOW A DESCENT TRAJECTORY MATCHED WITH A TIME SCHEDULE - The present invention relates to a method and a system used by an aircraft to follow a descent trajectory matched with a time schedule. The method is characterized in that the speed of the aircraft is servo-controlled to the speed required to comply with the time schedule by adjusting the pitch angle when the aircraft is not below the planned altitude on the trajectory beyond a threshold and by adjusting the engine thrust when the aircraft is below the planned altitude on the trajectory beyond the threshold. | 09-04-2008 |
| 20120232723 | Method to Increase Aircraft Maximum Landing Weight Limitation - A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow for a reduction in aircraft sink-speed assumptions. To further allow the aircraft to operate an increased maximum landing weight limitation. A system for use in measuring aircraft vertical velocity at initial contact with the ground, experienced while aircraft are executing either normal or hard landing events. Pressure sensors are attached to the working pressure within the landing gear strut, so to monitor in-flight landing gear strut pre-charge pressure, until such time as the pre-charge pressure suddenly increases, to detect the aircraft has come into initial contact with the ground. Rotation sensors are attached to the hinged elements of the landing gear strut, so to monitor in-flight landing gear strut extension, until such time as the strut extension suddenly decreases, to detect the aircraft has come into initial contact with the ground. | 09-13-2012 |
| 20120265374 | AIRCRAFT VERTICAL TRAJECTORY OPTIMIZATION METHOD - An target vertical trajectory for a flight plan is produced using aircraft performance characteristics taking into account only the altitude constraints, but ignoring any speed and time constraints. The target vertical trajectory is evaluated for violations of altitude, speed, and time constraints and on the basis of other criteria. An alternative vertical trajectory is generated by randomly changing parts of the target vertical trajectory, and this alternative is likewise evaluated. If the child vertical trajectory has a more robust evaluation, it becomes to new target vertical trajectory; otherwise the previous target vertical trajectory remains in place. The alternative vertical trajectory generation process is performed repeatedly and over time the target vertical trajectory evolves toward an optimum trajectory solution. | 10-18-2012 |
| 701006000 | Angle of attack | 8 |
| 20100100261 | Method and Device of Terrain Avoidance for an Aircraft - According to the invention, an altitude profile (PA) representative of the terrain overflown by the aircraft (AC) is established, and then an altitude limit curve (C) which comprises an intersection with said profile (PA) upon the engagement of a terrain avoidance maneuver is determined. As soon as there is no longer any intersection of the limit curve (C) with the altitude profile (PA), said terrain avoidance maneuver is interrupted. | 04-22-2010 |
| 20100100260 | ALTERNATIVE METHOD TO DETERMINE THE AIR MASS STATE OF AN AIRCRAFT AND TO VALIDATE AND AUGMENT THE PRIMARY METHOD - A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack. | 04-22-2010 |
| 20120078450 | DISPLAY INFORMATION TO SUPPORT CLIMB OPTIMIZATION DURING CRUISE - Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft. | 03-29-2012 |
| 20100222944 | AUTOMATIC PILOT PITCH ANGLE COMPENSATION - A method, apparatus, and computer program product are present for operating an aircraft. Responsive to a command to hold an altitude of the aircraft, an adjustment to a pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft is identified using a lift for the aircraft to form an identified adjustment to the pitch angle to reduce altitude deviations from at least one of a change in configuration of a number of flight surfaces and changes in wind. The pitch angle of the aircraft is adjusted using the identified adjustment during flight. | 09-02-2010 |
| 20110054720 | STALL, BUFFETING, LOW SPEED AND HIGH ATTITUDE PROTECTION SYSTEM - A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings. | 03-03-2011 |
| 20090062973 | STALL, BUFFETING, LOW SPEED AND HIGH ATTITUDE PROTECTION SYSTEM - A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings. | 03-05-2009 |
| 20090157239 | Vertical Gust Suppression System for Transport Aircraft - A method for vertical gust suppression due to turbulence for an aircraft having at least one of direct lift control surfaces or pitch control surfaces. The method includes sensing atmospheric turbulence, measuring the sensed atmospheric turbulence to generate turbulence data, generating a command based on the turbulence data, and applying the command to aircraft controls to actuate the direct lift control surfaces or the pitch control surfaces based on the turbulence data. Therefore, an aircraft response to the actuation of the direct lift control surfaces or the pitch control surfaces reduces a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude or a structural load of the aircraft due to the turbulence. Thus, the method reduces the effects of vertical gusts of wind on the aircraft, improves the comfort level for aircraft passengers and crew, and reduces diversions the aircraft may take to avoid the turbulence. | 06-18-2009 |
| 20090132104 | LONGITUDINAL AND VERTICAL GUST FEED FORWARD COMPENSATION USING LATERAL CONTROL SURFACES - In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands. | 05-21-2009 |
