| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 701007000 | Air speed or velocity measurement | 51 |
| 20080234881 | VERTICAL SPEED AND FLIGHT PATH COMMAND ALGORITHM FOR DISPLACEMENT COLLECTIVE UTILIZING TACTILE CUEING AND TACTILE FEEDBACK - A flight control system includes a collective position command algorithm for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command algorithm utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a “level flight” detent commands vertical velocity or flight path angle. The “level flight” detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement. | 09-25-2008 |
| 20080243314 | Merging and spacing speed target calculation - Embodiments of the present invention provide methods, computer programs, and apparatus for adjusting a speed target of an aircraft. In particular, the adjustment of the speed target of the aircraft may allow that aircraft to maintain merging and spacing constraints with respect to a leading aircraft. According to one embodiment of the present invention, the speed target of an aircraft may be adjusted by obtaining a speed target, obtaining own ship track data for the aircraft, obtaining lead ship track data for a leading aircraft, and calculating a speed target adjustment based on the speed target, the own ship track data, the lead ship track data and merging and spacing constraints. | 10-02-2008 |
| 20080243315 | DEVICE AND METHOD FOR ASSISTING IN THE MANAGEMENT OF AN ENGINE FAILURE ON AN AIRCRAFT - A device and method for assisting in the management of an engine failure on an aircraft. | 10-02-2008 |
| 20080249672 | ALTITUDE AND ACCELERATION COMMAND ALTITUDE HOLD ALGORITHM FOR ROTORCRAFT WITH LARGE CENTER OF GRAVITY RANGE - A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands. This blending determines a trim attitude for a given rotorcraft flight condition. | 10-09-2008 |
| 20080269964 | SYSTEM AND METHOD FOR TRANSITIONING MAPS ON AERONAUTICAL DISPLAY - A system for transitioning navigation data on a mobile platform (such as a train, ship, aircraft or automobile) is provided. The system includes a source of navigation display data and an image control module. The image control module generates image data from the navigation display data based on a position of the mobile platform. The image data includes at least one first navigation display data at a first opacity and at least one second navigation display data at a second opacity. The second opacity is computed based on the position of the mobile platform. The system also includes a display device disposed within the mobile platform that displays the image data. | 10-30-2008 |
| 20080294307 | Aircraft Guidance Using Localizer Capture Criteria for Rectilinear Displacement Data - Systems and methods for aircraft guidance using a localizer capture criteria for rectilinear displacement data are disclosed. In one embodiment, the method includes determining a rectilinear deviation D between a current aircraft location and a final defined path (FDP) of an aircraft and determining a location at which the aircraft should begin a reposition maneuver based on the rectilinear deviation D. The method starts a reposition maneuver of the aircraft at a location determined based on a relationship between D and characteristics of the aircraft during the reposition maneuver. In some embodiments, the characteristics of the aircraft may include a velocity of the aircraft with respect to ground, an aircraft track angle, a heading of the FDP of the aircraft, a maximum allowed bank angle of the aircraft during a reposition maneuver, and a time allowance for aircraft rollup and rollout. | 11-27-2008 |
| 20080306639 | DEVICES AND METHODS FOR FILTERING TERRAIN AN OBSTACLE ANTI-COLLISION ALERTS FOR AIRCRAFT - The present invention relates to a device and methods for filtering anti-collision alerts for aircraft having a locating system charting the position of the aircraft and estimating the precision of its position. A navigation system of the aircraft calculates at least the actual speed of the aircraft, the speed instruction and a first deviation between the instruction and the actual speed, and the deviation being compared with a first reference overshoot threshold. An anti-collision system generates alerts. An alarms manager of the aircraft centralizes the alerts transmitted by the terrain anti-collision equipment of the aircraft to the crew. The alerts each posses a coding of the danger level, and the danger levels form part of a first predetermined set. The alert filter according to the invention filters sets of alerts according to the coding of their danger level. | 12-11-2008 |
| 20080312779 | FLIGHT MANAGEMENT COMPUTER WITH CONSIDERATION OF APPROACH SPEED CONSTRAINT - The flight management computer discloses and carried onboard an aircraft can be programmed with a newly apparent speed constraint while it ensures the guidance of the aircraft in the course of a landing runway approach. It then takes account of the speed constraint by using it as target speed, when it is greater than an instruction speed which depends on the number of extended flap settings and which corresponds to the addition of a further flap setting. If appropriate, the speed constraint may be bounded below, thus making it possible to remain within the limits of the flight domain of the aircraft in its configuration at the time. | 12-18-2008 |
| 20090093919 | METHOD AND A DEVICE FOR OBTAINING A PREDICTIVE VERTICAL SPEED OF A ROTORCRAFT - The present invention relates to a method and a device for obtaining a predictive vertical speed of a rotorcraft, the device constituting a predictive vertical speed indicator ( | 04-09-2009 |
| 20090222150 | System for monitoring anemobaroclinometric parameters for aircraft - The disclosed embodiments concern a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes
| 09-03-2009 |
| 20090259351 | METHOD AND DEVICE FOR GUIDING AN AIRCRAFT - The device ( | 10-15-2009 |
| 20090281684 | FLIGHT GUIDANCE AND NAVIGATION DISPLAY FOR A HELICOPTER - A flight guidance and navigation display ( | 11-12-2009 |
| 20090319101 | FORMATION FLIGHT CONTROL METHOD - The invention relates to a method for controlling the formation flight of at least two aircraft ( | 12-24-2009 |
| 20100023187 | SYSTEM AND METHOD FOR DISPLAYING CONSTRAINT INFORMATION ON A GRAPHICAL AIRCRAFT INSTRUMENT TAPE ELEMENT - A flight deck display system for an aircraft includes a processor architecture configured to receive aircraft instrument data (e.g., altimeter or airspeed) and position data for the aircraft and, based upon the instrument data and the position data, generate image rendering display commands. The system also includes a display element configured to receive the image rendering display commands and, in response thereto, to render a graphical instrument tape. The instrument tape includes a graphical representation of a scrolling altitude or airspeed range that dynamically scrolls in response to changes in the altitude/airspeed data, along with a graphical representation of a position-dependent altitude/airspeed clearance element that conveys an altitude/airspeed restriction for an approaching geographic position of the aircraft. The content of the position-dependent clearance element is influenced by the position data. | 01-28-2010 |
| 20100036549 | METHODS AND SYSTEMS FOR DISPLAYING A PREDICTED DISTRIBUTION OF FIRE RETARDANT MATERIAL FROM AN AIRCRAFT - Systems and apparatus are provided for using a flight management system in an aircraft for airborne fire fighting. An apparatus is provided for a display system for use in an aircraft equipped for transporting a fire retardant material. The display system comprises a display device associated with the aircraft, and a flight management system coupled to the display device. The flight management system is adapted to control the rendering of a navigational map on the display device, determine a predicted distribution region for a release of the fire retardant material, and overlay a graphical representation of the predicted distribution region on the navigational map. | 02-11-2010 |
| 20100152930 | Method for Determining the Speed of an Aircraft - The invention relates to a method for determining the speed of an aircraft that is subject to a time constraint. The invention consists no longer in calculating a single CAS/MACH pair during climb/descent but in adapting the speed in a continuous manner to the bounds of curves of minimum V | 06-17-2010 |
| 20100250030 | SYSTEM AND METHOD FOR RENDERING VISIBLE FEATURES OF A TARGET LOCATION ON A SYNTHETIC FLIGHT DISPLAY - A flight deck display system for an aircraft or other vehicle includes a first data source of visual feature data that is indicative of visual features of a location of interest, a second data source of flight data for the aircraft, a processor architecture, and a display element. The processor architecture is operatively coupled to the first data source and to the second data source, and it is configured to process the visual feature data, process the flight data, and, based upon the visual feature data and the flight data, generate image rendering display commands. The display element receives the image rendering display commands and, in response thereto, renders a dynamic graphical representation of the location of interest using the visual feature data. The dynamic graphical representation of the location conveys an amount of visible detail that varies as a function of the flight data. | 09-30-2010 |
| 20100286850 | Standby Instrument for Aircraft - The invention relates to a standby instrument for the piloting of aircraft allowing a pilot to restore a display similar to that of a head-up display in the event that the latter should fail. According to the invention, the standby instrument comprises means for determining and displaying a speed vector ( | 11-11-2010 |
| 20110184592 | ALTERNATE AIRSPEED COMPUTATION WHEN AIR DATA COMPUTER (ADC) FAILS - An avionics system comprising a primary airspeed data source and a flight management computer is provided. The primary airspeed data source is configured to calculate a primary airspeed. The flight management computer is configured to use airspeed as an aid to control an aircraft, wherein the flight management computer is further configured to determine an alternative airspeed for use by the flight management computer as an aid to control an aircraft when the primary airspeed is unavailable. | 07-28-2011 |
| 20110202208 | METHOD AND SYSTEM FOR PREDICTING PERFORMANCE OF AN AIRCRAFT - Methods and systems for operating an avionics system on-board an aircraft are provided. A plurality of signals representative of a current state of the aircraft are received. A future state of the aircraft is calculated based on the plurality of signals representative of the current state of the aircraft. An indication of the future state of the aircraft is generated with the avionics system on-board the aircraft. | 08-18-2011 |
| 20110264308 | Method And Device For Automatically Estimating An Air Speed Of An Aircraft - The device ( | 10-27-2011 |
| 20110270473 | SYSTEMS AND METHODS FOR PROVIDING A VERTICAL PROFILE FOR AN IN-TRAIL PROCEDURE - A vertical profile for an in-trail procedure can provide a pilot with enhanced situational awareness. Such a vertical profile may be able to provide a graphical indication of a clearance window for change in altitude procedures, as well as the underlying bases for such a window. A method can include providing, in a hardware display, a graphical vertical profile displaying an aircraft to a pilot of the aircraft. The method can also include providing, in the vertical profile, an indication of the relative speed of at least one other aircraft and a graphical indication of a clearance window for vertical maneuvers for the aircraft of the pilot. | 11-03-2011 |
| 20110270474 | Control System for Vehicles - A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces. | 11-03-2011 |
| 20120303184 | Combined Stand-by Instrument and Method for Calibrating the Combined Stand-by Instrument - A combined stand-by instrument intended to be fitted to the instrument panel of an aircraft, and a method for calibrating the combined stand-by instrument, comprises anemobarometric sensors, inertial sensors, a magnetic field sensor, a screen and a computer making it possible to determine and to display on the screen an altitude, a speed, an attitude and a current heading of the aircraft on the basis of the sensors and to calibrate the magnetic field sensor. The computer is configured to allow the simultaneous display on the screen of the altitude, of the speed and of the attitude of the aircraft as well as a guide for the calibration of the magnetic field sensor. | 11-29-2012 |
| 20130030611 | METHOD AND DEVICE FOR AN OPTIMAL MANAGEMENT OF THE VERTICAL TRAJECTORY OF AN AIRCRAFT - The device ( | 01-31-2013 |
| 20130035809 | METHOD AND SYSTEM FOR DETERMINING FLIGHT PARAMETERS OF AN AIRCRAFT - According to the invention, the system for determining, in real time, flight parameters of an aircraft, in the course of a flight of the latter, comprises an extended Kalman filter ( | 02-07-2013 |
| 20130066486 | SYSTEM AND METHOD OF DISPLAYING AIRSPEED INFORMATION FOR AN AIRCRAFT - A method and a system are provided for displaying flight information of an aircraft. The system receives at least one user defined airspeed related to flight of the aircraft from a user. A processor calculates the at least one calculated airspeed based on data stored in a memory device. A static position is determined by the processor for the user defined and calculated airspeeds. The difference between the positions developed from the user defined and calculated position is also calculated. A difference indicator is displayed to the user for the difference between each user defined and calculated position. | 03-14-2013 |
| 20130173091 | EARLY IDENTIFICATION OF A VORTEX RING PHASE - The invention relates to a method for early detection of the vortex ring state in a helicopter, having the following steps:
| 07-04-2013 |
| 20130211634 | METHOD AND SYSTEM FOR PROVIDING SIDESLIP ENVELOPE PROTECTION - A system for providing sideslip envelope protection includes a processor for obtaining values of a sideslip envelope indicative of operating conditions of the aircraft along an axis and for estimating a sideslip angle along the axis from at least one operating condition; and a comparer for comparing the sideslip angle with the sideslip envelope to generate an output value, where the processor determines a maximum yaw rate from the output value and scales the maximum yaw rate to generate a scaled yaw rate. | 08-15-2013 |
| 20140052314 | SYSTEMS AND METHODS FOR MONITORING LOW SPEED OF A ROTORCRAFT - Systems and methods to provide alerts when a rotorcraft is in a low airspeed condition. During takeoff or go-around, an aural alert is provided to the pilot before the aircraft slows to less than the effective translational lift speed. The aural, visual, and/or tactile alert gets the pilot's attention to manage the aircraft's airspeed before it is too late in this critical flight phase. | 02-20-2014 |
| 20140129057 | PASSIVE LOCAL WIND ESTIMATOR - Local wind fields can be predicted if both the airspeed and the ground speed of the helicopter are known. An aircraft that uses an inertial navigation unit, autopilot and estimator allows a measure of ground speed to be known with good certainty. The embodiments herein extends this system to allow an estimate of the local wind field to be found without actively using an airspeed sensor, but instead combining the measurements of an accelerometer and a drag force model and a model of controlled aerodynamics of the aircraft to estimate the airspeed, which again can be used to estimate the local wind speed. | 05-08-2014 |
| 20140343761 | SYSTEM AND METHOD FOR PERFORMING AN AIRCRAFT AUTOMATIC EMERGENCY DESCENT - A system and method automatically control an emergency descent of an aircraft to a target altitude. Factors including weather, traffic, terrain, special use airspace, distance to an alternate, time above 10,000 feet, and time airborne are considered in deciding on descent airspeed, aircraft heading, and selection of an alternate. The target altitude may be redefined after activation of a Terrain Advisory and Awareness System. A vertical speed, or rate of descent, may be adjusted after receiving a resolution advisory from a traffic clearance and avoidance system if the maneuver with maximum operating speed generates excessive normal acceleration. Initiation of the emergency descent will be transmitted via radio and data link communication and automatic selection of a mode declaring a state of emergency on the traffic clearance and avoidance system. | 11-20-2014 |
| 20150100184 | SYSTEM AND METHOD FOR COMPUTING MACH NUMBER AND TRUE AIRSPEED - A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable. | 04-09-2015 |
| 20150149000 | Unkown - The drone comprises: a vertical-view camera ( | 05-28-2015 |
| 20150331420 | Methods and Systems for Conserving Power During Hover Flight - An example method may include determining a drag force of an apparent wind on an aircraft that is coupled to a ground station via a tether. The method also includes determining a trajectory of the aircraft to a point downwind of the ground station such that the aircraft travelling the trajectory causes the tether to unfurl along a catenary path above ground. The method further includes determining an orientation of the aircraft to travel the trajectory in the apparent wind so that an actuator of the aircraft is configured to provide a vertical thrust in a direction substantially perpendicular to the ground. The method also includes determining a vertical thrust for the aircraft at the orientation to travel the trajectory in the apparent wind. The method also includes providing instructions to cause the actuator of the aircraft to provide the vertical thrust to move the aircraft along the trajectory. | 11-19-2015 |
| 20150360794 | ROTORCRAFT HAVING AN AIRSPEED SENSOR LOCATED AT THE TOP OF A TAIL FIN OF THE ROTORCRAFT - A method of calculating and displaying the true airspeed of a rotorcraft. At least one omnidirectional airspeed sensor is installed at the top of a tail fin of the rotorcraft. The true airspeed of the rotorcraft flying at speeds that are lower than or equal to at least one airspeed threshold of the rotorcraft is calculated by correcting the measurements supplied by the airspeed sensor installed at the top of the tail fin as a function of the effects produced by the air stream generated by rotation of the main rotor of the rotorcraft on the characteristics of the speed of the air stream measured by the tail fin airspeed sensor. For this purpose, a correction rule calibrated in test flight is advantageously applied to correct the measurements supplied by the airspeed sensor installed at the top of the tail fin. | 12-17-2015 |
| 20160004255 | AIRCRAFT CONTROL METHOD - A computer-implemented method of controlling an aircraft including, determining whether a change in altitude at a predetermined thrust-setting can be performed, the determination including: determining a climb-requirement including initial and final altitudes and a required range of airspeeds at the final altitude; determining aircraft performance data including a thrust at the final altitude at the thrust-setting, an initial airspeed at the initial altitude and an aircraft total mass at the initial altitude; using the aircraft performance data to determine a final airspeed and drag at the final altitude if a change in altitude at the predetermined setting were performed; determining whether thrust at the final altitude at the thrust-settings and airspeed is greater than drag; and providing a signal indicating whether the calculated final airspeed falls within the required range of airspeeds, and whether the thrust at the final altitude and airspeed at the cruise thrust-setting is greater than drag. | 01-07-2016 |
| 20160009390 | UNMANNED AERIAL VEHICLE AND METHODS FOR CONTROLLING SAME | 01-14-2016 |
| 20160019795 | FLIGHT TRAJECTORY OPTIMISATION AND VISUALISATION TOOL - A method and system and tools for optimizing an aircraft flight trajectory that determine an advantageous flight profile that takes into account developing operational conditions, air traffic constraints and aircraft performance in a timely manner that can allow tactical flight plan changes to be incorporated without unduly introducing operational or financial penalties to the operator. | 01-21-2016 |
| 20160026190 | Adaptable Automatic Nacelle Conversion for Tilt Rotor Aircraft - Systems and methods for displaying to a tilt rotor aircraft pilot an optimum nacelle position and/or automatically controlling movement of the nacelles for the pilot. An automatic nacelle conversion function employs an active flight director speed mode to provide a current desired speed and a final speed. When the automatic nacelle conversion function is in a passive (uncoupled) mode of operation, the pilot follows visual cues, manually achieving the commanded nacelle position by rotating a thumbwheel. When in an active (coupled) mode of operation, the automatic nacelle conversion function provides a fully automatic nacelle controller requiring no pilot input. This automatic nacelle controller provides a variable nacelle rate along with several angle versus speed schedules tailored for different guidance speed modes and a wide range of aircraft configurations. The automatic nacelle conversion function is improved though the inclusion of altitude, rate of climb, and deceleration rate commands. | 01-28-2016 |
| 20160046386 | LANDING AID METHOD AND DEVICE FOR AN AIRCRAFT - A landing aid method and device for an aircraft including a unit for calculating automatically in a repetitive manner, during a final approach of the aircraft with a view to landing on a landing runway, using at least a ground speed of the aircraft, a height of the aircraft in relation to the ground, and a target vertical speed representing a vertical speed required on contact with the landing runway, a slope angle of a flight path allowing the aircraft to perform a flare, checking at least the target vertical speed on contact with the landing runway, and a unit for displaying automatically, on at least one screen of the flight deck of the aircraft, a first symbol illustrating the current slope angle of the aircraft and a second symbol illustrating the calculated slope angle. | 02-18-2016 |
| 20160047628 | METHODS AND APPARATUSES FOR AERIAL INTERCEPTION OF AERIAL THREATS - Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle. | 02-18-2016 |
| 20160070263 | METHOD AND DEVICE FOR AUTOMATIC PROTECTION OF AN AIRCRAFT AGAINST A RISK OF COLLISION WITH THE GROUND - A protection device including a unit for implementing a protection function that prevents the aircraft from flying under a given height with respect to the ground. The device includes a unit for determining the current values of parameters, and at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip. A calculation unit is provided for calculating, during a landing on the landing strip, from data including said current values, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function. A checking unit is provided for checking whether a condition dependent on the current longitudinal distance is met, the protection function being automatically deactivated if the checking unit concludes that this condition is met. | 03-10-2016 |
| 20160102994 | SYSTEMS AND METHODS FOR ATTITUDE FAULT DETECTION BASED ON AIR DATA AND AIRCRAFT CONTROL SETTINGS - Systems and methods for attitude fault detection based on air data and aircraft control settings are provided. In one embodiment, a sensor monitor for an aircraft attitude measurement system comprises: an aircraft model configured to model a plurality of states, the plurality of states including at least an aircraft attitude state, an aircraft velocity state, a sink rate error state, and a wind velocity state; a propagator-estimator configured to utilize the plurality of states of the aircraft model to process air data measurements and attitude measurements from a first inertial measurement unit of the aircraft attitude measurement system; and a residual evaluator configured to input residual error values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the residual error values exceed a predetermined statistical threshold. | 04-14-2016 |
| 20160107766 | SYSTEM AND METHOD FOR DISPLAYING RUNWAY LANDING INFORMATION - A system and method are disclosed for indicating to an aircrew of an aircraft a normalized runway icon to ensure visualization of a predicted touchdown point, runway length, stopping distance, energy state marking, and threat conditions, where normalization is referenced to typically available length for landing. Indications of present aircraft locations relative to the icons as well as alerts when thresholds are exceeded are provided. | 04-21-2016 |
| 20160161949 | AIRCRAFT WING STRUCTURE AND CONTROL SYSTEM - An aircraft includes a wing. The wing includes an aileron pivotally connected to a trailing edge of the wing, and a Lam aileron pivotally connected to the trailing edge of the wing. The aircraft includes a motor connected to the Lam aileron and configured to rotate the Lam aileron. The aircraft includes a controller configured to detect a deflection of the aileron from a neutral position, calculate a target deflection for the Lam aileron using the deflection of the aileron, and cause the motor to rotate the Lam aileron to the target deflection. | 06-09-2016 |
| 20160176522 | METHOD AND A SYSTEM FOR DETERMINING AN ANGULAR VELOCITY IN TURNING FOR A ROTARY WING AIRCRAFT | 06-23-2016 |
| 20160179327 | HUMAN MACHINE INTERFACE DEVICE FOR AIRCRAFT | 06-23-2016 |
| 20160187882 | MODULAR FLIGHT MANAGEMENT SYSTEM INCORPORATING AN AUTOPILOT - A modular vehicle management system is described, comprising a controller module configured to control different types of carrier modules. The controller module includes a computer system and optionally one or more sensors. The computer system is configured to perform operations comprising detecting whether a carrier module is connected to the controller module. If the carrier module is connected to the controller module, the carrier module is authenticated. If the authentication fails, operation of the vehicle is inhibited. The control module is configured to determine carrier module capabilities including information regarding a navigation processing device, and/or a radio modem. The controller adapts to the capabilities of the controller module. Using information from the sensors and the navigation processing device, the vehicle management system navigates the vehicle. | 06-30-2016 |
| 20160251086 | SERVO TRANSPARENCY WARNING SYSTEM AND METHOD | 09-01-2016 |
| 20160378121 | LANDING AIRCRAFTS WITH OPTIMAL LANDING SPOT SELECTION - Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for landing aircrafts with optimal landing spot selection. In one aspect, a method includes initiating an autorotation of an aircraft in response to detecting all engine failure, determining a plurality of flight characteristics and conditions of the aircraft at a time of initiating the autorotation, the plurality of flight characteristics and conditions comprising an aircraft altitude, an aircraft velocity, and wind direction, determining total air-time for glideslope and flare control, and a geographic area within which to land the aircraft by autorotation based on the plurality of flight characteristics and conditions, and controlling the aircraft to land the aircraft by autorotation within the geographic area. | 12-29-2016 |
