| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 701005000 | Rate of change (e.g., ascent, decent) | 39 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20110202207 | Method And Device For Automatically Protecting An Aircraft Against An Excessive Descent Rate - The device ( | 08-18-2011 |
| 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 |
| 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 |
| 20130006448 | METHOD OF DYNAMICALLY CONTROLLING THE ATTITUDE OF A DRONE IN ORDER TO EXECUTE A FLIP TYPE MANEUVER AUTOMATICALLY - This method controls the drone in order to flip through a complete turn about its roll axis or its pitching axis. It comprises the steps of: a) controlling its motors simultaneously so as to impart a prior upward vertical thrust impulse to the drone; b) applying different and non-servo-controlled commands to the motors so as to produce rotation of the drone about the axis of rotation of the flip, from an initial angular position to a predetermined intermediate angular position; and then c) applying individual control to the motors, servo-controlled to a reference target trajectory, so as to finish off the rotation of the drone through one complete turn about the axis of rotation, progressively from the intermediate angular position with a non-zero angular velocity to a final angular position with a zero angular velocity. | 01-03-2013 |
| 20140236400 | Laser Landing Altimeter for Precision Aircraft Landing Aid - The present invention discloses a laser landing altimeter for precision aircraft landing aid. Its measurement unit measures distance using a modulated laser beam with centimeter accuracy. Its processing unit predicts the future altitude based on a realistic landing altitude model and determines the landing maneuver time (the time to initiate a landing maneuver). | 08-21-2014 |
| 20150316931 | METHOD AND SYSTEM FOR CONTROLLING A FLYING WING - The invention relates to a method for control of a flying wing. The flying wing is arranged to be controlled to move along a predetermined trajectory by means of a fluid stream passing a wing of the flying wing. The flying wing comprises at least one control surface for controlling the movement of the flying wing along the predetermined trajectory. The flying wing is positioned in a reference frame where the x-axis is directed horizontally along a level L above which the flying wing moves, the y-axis is perpendicular to the x-axis in a vertical direction and the z-axis is perpendicular to the x-axis along the level L in a direction along the principal direction of the fluid stream. The invention further relates to a system comprising a flying wing and a computer-readable medium for use with a flying wing. | 11-05-2015 |
| 20150338853 | Determining a descent trajectory described by an Aircraft Intent Description Language (AIDL) - Determining a descent trajectory described by an Aircraft Intent Description Language (AIDL) is disclosed. An example method includes accessing historical flight data for a recorded flight trajectory, the recorded flight trajectory having been performed by a first aircraft type of multiple aircraft types and for a first airline of multiple airlines; estimating, using a processor, an aircraft intent parameter and an initial condition of the recorded flight trajectory based on an aircraft intent description language (AIDL) representation of the recorded flight trajectory; and mapping, using the processor, the aircraft intent parameter and the initial condition to a combination of the first aircraft type, the first airline, and an identified intended descent procedure. | 11-26-2015 |
| 20160026188 | METHOD AND DEVICE FOR AUTOMATICALLY ENGAGING AN AUTOMATED EMERGENCY DESCENT OF AN AIRCRAFT - A device for automatically engaging an automated emergency descent of an aircraft. The device comprises a monitoring unit configured to automatically compare, repetitively, a current cabin altitude of the aircraft to an engagement threshold representing an altitude value, an activation unit configured to automatically engage the automated emergency descent when the current cabin altitude reaches the engagement threshold called main engagement threshold, and a unit for generating at least one engagement threshold configured at least to adapt the main engagement threshold according to the terrain, the main engagement threshold corresponding to the sum of a terrain altitude and a predetermined margin. | 01-28-2016 |
| 20160085239 | METHOD OF ADAPTING A SEGMENT OF AN AIRCRAFT TRAJECTORY WITH CONSTANT GROUND GRADIENT SEGMENT ACCORDING TO AT LEAST ONE PERFORMANCE CRITERION - A method for adapting an aircraft constant-gradient descent segment comprises: an acquisition step in which state variables characterizing the aircraft, environment variables characterizing the environment thereof and path variables characterizing the predicted path thereof at one of the initial and final points of the segment are acquired; a calculation step whereby a limit ground gradient for at least one performance criterion is calculated from the state variables, environment variables and path variables; a validity verification step checking the validity of the path initially predicted against the most restrictive limit ground gradient; and when the path initially predicted is not valid: a feasibility verification step checking the feasibility of a command to modify at least one state variable; if feasibility is verified, a prediction of executing the command; otherwise, a prediction of modifying one of the initial and final points of the segment with respect to constraints of the flight plan. | 03-24-2016 |
| 20160194074 | Systems And Methods For Aircraft Control Surface Hardover And Disconnect Protection | 07-07-2016 |
| 20160194089 | VEHICLE ATTITUDE CONTROL USING JET PADDLES AND/OR MOVABLE MASS | 07-07-2016 |
| 20160379501 | METHODS AND SYSTEMS FOR CONTROLLING THE FLIGHT OF AIRCRAFT - Methods and systems for controlling the flight of aircraft are disclosed. An example method includes in response to a first time of arrival at a first waypoint, determining first cruise speeds and corresponding first descent speeds for the first waypoint at the first time of arrival; in response to a second time of arrival at a second waypoint, determining second cruise speeds and corresponding second descent speeds for the second waypoint at the second time of arrival, at least one of the first waypoint or the second waypoint being in a descent phase of a flight; identifying a third cruise speed and a third descent speed based on the first cruise and descent speeds and the second cruise and descent speeds, the first cruise and descent speeds including the third cruise speed and the third descent speed, the second cruise and descent speeds including the third cruise speed and the third descent speed; and identifying a trajectory of an aircraft that satisfies the third cruise speed and the third descent speed. | 12-29-2016 |
| 20190146524 | METHOD AND DEVICE FOR TERRAIN SIMULATION FLYING OF UNMANNED AERIAL VEHICLE AND UNMANNED AERIAL VEHICLE | 05-16-2019 |
| 701006000 | Angle of attack | 12 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 20130197724 | GUST COMPENSATED TOTAL ENERGY VARIOMETERS - Rise and fall rates for a glider are determined based on the glider's angle of attack and speed. These rise and fall rates are used to compensate a variometer so that the impact of vertical airmass flow can be used to optimize glider soaring. Altitude measurements are used to determine the glider's potential energy while velocity is used to determine the glider's kinetic energy. Total energy compensation techniques are then used to correct error calculations in the variometer. | 08-01-2013 |
| 20150329216 | MEASUREMENT SYSTEM FOR MEASURING THE VELOCITY OF AN AIRCRAFT - The disclosure herein relates to a measurement system to measure characteristics of the velocity vector of an aircraft in relation to a surrounding air mass, the measurement system comprising—a frontal surface of the aircraft, two primary sensors, each being fixed to the frontal surface of the aircraft and able to deliver an output value relating to the deformation experienced by the sensor, and a processing unit able to receive the output values and able to calculate the angle of attack and/or the velocity of the aircraft on the basis of these output values. | 11-19-2015 |
| 20150360767 | METHOD AND DEVICE FOR GENERATING AT LEAST ONE SET POINT FROM A FLIGHT CONTROL SET POINT, A MOTOR CONTROL SET POINT AND AN AIRCRAFT GUIDANCE SET POINT, RELATED COMPUTER PROGRAM PRODUCT AND AIRCRAFT - A method and device for generating at least one set point from a flight control set point, a motor control set point and an aircraft guidance set point, a related computer program product and an aircraft are disclosed. In one aspect, the method includes acquiring a mechanical property relative to at least one corresponding primary control member and computing at least one set point from among one or more primary set points and one or more secondary set points. The method also includes generating at least one of the computed set point(s) and switching, based on the mechanical property acquired for the corresponding primary control member, between a first mode in which one or more primary set points are generated and a second mode in which one or more secondary set points are generated. | 12-17-2015 |
| 20160041561 | Aircraft Flying Aid - An aircraft flying assist device, system, and method are disclosed. The aircraft flying assist device can include a computation module to receive data from a distance sensor to determine a height above ground between an aircraft and an underlying ground surface, and to determine a vertical velocity of the aircraft. The aircraft flying assist device can also include a command module to determine a flight instruction command to guide a pilot of the aircraft using at least one of the height above ground and the vertical velocity. The flight instruction command can be an aural command deliverable to the pilot via an audio output mechanism. | 02-11-2016 |
