Abstract: A system and method displays an intercept point on a synthetic vision display that conforms to the flight path intercepting the terrain when the nose of the helicopter is pitched up during landing. A steep approach during landing may be detected by an evaluation of, for example, attitude of the helicopter, rate of descent, and airspeed.

Abstract: A beacon receiving system on a pallet of a container cargo bundle is airdropped from a cargo airplane. The beacon receiving system comprises a sensor that detects during descent a beacon signal generated from a beacon placed at the target drop location. The sensor provides signals to a microcontroller that ascertains an angle at which the beacon signal is received. An inertial measurement unit provides signals indicating a tilt of the pallet during descent, which is used by the microcontroller to determine an offset angle of the received beacon signal. This information is used to steer the container cargo bundle during descent to achieve high precision in landing at the desired target drop location. The beacon signal may comprises a modulated light signal which can be distinguished by the sensor from other light sources.

Abstract: The present invention provides a method of modifying the pitch attitude of an aircraft during landing, comprising: commanding the flaps to move to a landing setting; providing a current value for a flight condition parameter; providing a current flaps setting; comparing said current value to at least one threshold value; if said current value exceeds said threshold, determining a new flaps setting capable of producing an improvement in at least one of a selected aft body contact margin and a selected nose gear contact margin for the aircraft; and adjusting the flaps to said new flaps setting.

Abstract: The device includes elements of a processing unit which determine a limit trajectory representing a flight trajectory which is compatible with the aircraft performance during the approach and which shows the limits for the flight of the aircraft. For example, a vertical profile and a horizontal trajectory are determined, with the horizontal trajectory being non-linear so that the energy of the aircraft can be sufficiently dissipated before final approach along an approach axis, while also avoiding obstacles. Thus, a flight trajectory is determined even when the aircraft has deviated from a flight plan and approach axis.

Abstract: Systems and methods for runway condition alert and warning. The system can include a first measurement system disposed on a first aircraft, the first measurement system adapted to gather telemetry inputs associated with a braking action value of the first aircraft on an airport runway. The system can also include a second measurement system disposed on a second aircraft, the second measurement system adapted to gather telemetry inputs associated with a braking action value of the second aircraft on the airport runway. The system can also include a computer adapted to receive and sort the telemetry inputs from the first and second aircraft. The computer can be adapted to utilize the telemetry inputs to predict an expected future braking action value for a third aircraft scheduled to utilize the airport runway.

Abstract: A method and apparatus for displaying an energy state of an aircraft. The energy state of the aircraft is identified by a processor unit based on a speed of the aircraft and an altitude of the aircraft. An indication of the energy state is displayed by the processor unit.

Abstract: The method according to the invention comprise the following steps, dynamic measurement of the current geographical position of the aircraft, and its current ground speed, calculation of a first length representative of a flight phase of the aircraft, and calculation of a second length representative of a ground phase of the aircraft, calculation of the position of the stop point based on the first length, the second length and the current geographical position. The calculation of the first length comprises a phase for dynamically estimating a distance traveled by the aircraft during at least part of a flare phase of the aircraft.

Abstract: A method and system is described for enhancing ground situational awareness to an aircrew via the display of an airport moving map within an own-ship, including determining the position of the own-ship and an aircraft on one of a taxiway, a runway, or an apron, displaying each of the own-ship and the aircraft on an airport moving map by displaying for each a first symbol that indicates the location on the airport moving map; and displaying a second symbol that changes in transparency in proportion to the range of the airport moving map.

Abstract: Addressed are systems and methods for providing to pilots of landing aircraft real-time (or near real-time) information concerning runway conditions and aircraft-stopping performance to be encountered upon landing. The systems and methods contemplate using more objective data than utilized at present and providing the information in automated manner. Information may be obtained by using conventional ground-based runway friction testers or, advantageously, by using air-based equipment such as (but not limited to) unmanned aerospace vehicles (UAVs).

Abstract: An electronic flight bag apparatus includes an electronic flight bag (EFB) system installed in an aircraft and which interfaces with a ground network, and a portable EFB device connectible with the EFB system via a trusted secure connection. This apparatus makes it possible for a flight crew member to remove the portable device from the aircraft, enter flight information into the device in a convenient manner, and transfer the information to the installed EFB system. Auxiliary crew members may use the portable device during flight to assist the flight crew.

Abstract: A method and device are provided for determining a target altitude for an emergency descent of an aircraft that is to be reached by the end of the emergency descent. The device determines an updated target altitude which takes into account variations of barometric pressure and which is able to replace the target altitude that must be reached at the end of the emergency descent. The method includes determining an initial target altitude representative of the initial position of the aircraft and then repeatedly determining a current target altitude along a reference horizontal distance. The current target altitude is compared to the initial target altitude and is used to update the emergency descent if the current target altitude is lower than the initial target altitude.

Abstract: Present novel and non-trivial system, device, and method for generating location information presented to a pilot are disclosed. A processing unit is configured to receive manual input data representative of one or more selected image location(s) on a first image data set; determine a selected geographic location for each selected image location; and update the second image data set to include location pointer data. As embodied herein, first and second images represented in the first and second image data sets, respectively, could be displayed simultaneously on the same display unit or separately on different display units. Also, the first image and second image could correspond to an egocentric view and a plan view, respectively, or vice-versa. Additionally, the first image data set and/or second image data set could be updated include first and/or second location pointer data, respectively.

Abstract: A method of extending the operation of an unmanned aerial vehicle (UAV) is disclosed. The method comprises detecting that an energy storage device on board the UAV is depleted below a threshold level, landing the UAV at a base station, and initiating operation of the base station to cause a replacement mechanism thereof to remove the energy storage device on board the UAV from the UAV and to replace this with another energy storage device.

Abstract: A system and method are provided for advising a pilot if it is safe to continue an approach to landing in adverse weather conditions. The system considers flight parameters from the flight management system, stored runway situational parameters, and weather information. The weather information may include, for example, reports, forecasts, and data collected in real time. The advice may be display as one of a plurality of recommendations based on a comparison of the weather information to a threshold.

Abstract: A computer implemented method, apparatus, and computer usable program product for cross checking required navigation performance procedures. A required navigation performance procedure in a flight management system is executed in an aircraft. A global positioning system signal in an electronic flight bag or other independent data processing system located onboard the aircraft is received while executing the required navigation performance procedure. A current position of the aircraft based on the global positioning system signal is presented on a moving map. A set of containment lines on the moving map are displayed to indicate whether deviations from the required navigation performance procedure have occurred.

Abstract: A method and apparatus for simulating effects of threats to aircraft communications. A simulation of an aircraft environment is run with the aircraft communications in an aircraft communications network in the aircraft environment. A number of conditions is introduced. The number of conditions comprises a threat configured to affect the aircraft communications in the aircraft communications network in an undesired manner. A change in traffic flow of aircraft in an airspace in the aircraft environment is identified in response to the number of conditions.

Abstract: A method is provided for displaying information on a display device of an aircraft. The method comprises determining graphics data for visual aids that represent missed approach data; incorporating the graphics data into a user interface that is in perspective view; and generating the user interface for display on the display device of the aircraft.

Abstract: A computer-implemented method, system, and/or computer program product evaluates a real-time condition of a construct of an airport runway. A processor receives a set of temporally-spaced runway vibrations. This set of temporally-spaced runway vibrations is measured by a set of smart sensors on an airport runway after a landing aircraft touches down on the airport runway. Using data that describes the set of temporally-spaced runway vibrations as inputs to an analysis algorithm, a real-time physical condition of a construct of the airport runway is determined.

Abstract: Method and device for aiding the piloting of an airplane during a landing phase for ensuring, during rollout on a landing runway, that in the nominal case the airplane will stop level with a selected exit, while guaranteeing that in the case of a fault the airplane will stop before the end of the runway.

Abstract: A method and system for managing automatic guidance of an aircraft during a complete engine failure. Said system includes means for monitoring engines so as to be able to detect a complete failure of the engines; means for detecting whether the aircraft is in flight; means for detecting whether the aircraft is in a different guidance mode from a guidance mode configured to make the aircraft descend with a reduced engine thrust and a fixed speed; and control means for automatically bringing guidance means of the aircraft into a guidance configuration compatible with the situation associated with the complete failure of the engines.

Abstract: A computer network for calculating a value for the true braking coefficient of friction for an aircraft runway or taxiway using data from one or more aircraft's flight data recorders or flight data management systems, and reporting the calculated value information to individuals and agencies including air traffic control, airport operations and maintenance, and aircraft pilots and ground crews is described and claimed herein. The data may be obtained in real-time by either an onboard or an off-aircraft high-power computing system, calculating the aircraft's true braking coefficient of friction, and reporting the calculated information to the individuals and agencies.

Abstract: A vehicle display system diminishes specified display features when in a taxi mode. EV images, SV images, and avionics symbology are displayed, with certain of the images and symbology being diminished when in a taxi mode. Additionally, guidance to the runway centerline is displayed in the taxi mode.

Abstract: Flight entries in a flight logbook maintained on a flight server are automatically generated using a remote location-aware mobile device. The remote location-aware device automatically detects aircraft takeoff and landing. The flight server posts designated flight information from the flight logbook to a plurality of social networks.

Abstract: A system and method of providing aerial navigation for an aircraft comprises presenting an enlarged virtual runway for an identified runway on a display, where the virtual area of the virtual runway remains substantially constant as the aircraft approaches the runway.

Abstract: A method for estimating a loading criterion relating to the load experienced by a structural component of an aircraft, and assistance with detecting a so-called “hard” landing. The method includes measuring parameters of the aircraft and calculating at least one loading criterion for the loading of the structural component using at least one neural network receiving the parameters as input. Assistance with detecting a hard landing then includes determining of a time of impact of the aircraft on a landing strip from the measured parameters, then estimating a plurality of the parameters at the determined time of impact so as to calculate the at least one loading criterion relating to the loading of the structural component.

Abstract: 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, or current intent 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.

Abstract: A method is provided to measure an aircraft under simulated flight-loads while the aircraft is not in flight. Simulated flight-loads may be applied to the aircraft, while the aircraft is not in flight, in order to substantially simulate flight pressure distribution loads the aircraft would experience during flight. A position of one or more portions of the aircraft may be measured, while the aircraft is under the simulated flight-loads, to determine an effect of the simulated flight-loads on the aircraft.

Abstract: An apparatus on an integrated circuit, and method thereof, provides a real-time flexible interface between inputs from a vehicle components and outputs to the vehicle control components. The functions comprises of a programmable interconnection matrix, engine sensors and a control interface. Both engine sensors and control functions comprise of fixed hardwired functions and a customization hardware area. The apparatus therefore provides means for flexible powertrain events control target for the next generation of low-polluting power trains of vehicles.

Abstract: A method for determining the distance of an aircraft from an offset runway during a landing by offset approach, the offset runway being situated at a distance D from a main runway equipped with at least one elevation beacon, comprises at least the following steps: determining the height h at which the aircraft is situated, height determined with respect to a point T1 of the offset runway, height measured by a radioaltimeter with which the aircraft is equipped, determining the angle of elevation ? of the MLS mode by using the information of the elevation beacon provided by an elevation beacon with which said main runway is equipped, determining the value of the distance ? of the aircraft from the azimuth beacon (10) by using the following formula ? = ( h Tan ? ( ? ) - D ? ? 2 Cos ? ( ? ) ) 2 + h 2 , and, using said distance ? to obtain a point of location of the aircraft in an offset runway reference frame.

Abstract: Methods and apparatus are provided for automated control of aerodrome lighting. An exemplary system includes a communication radio, an aerodrome lighting data source, and a processor. The communication radio is configured to selectively transmit radio frequency (RF) signals. The aerodrome lighting data source is configured to at least selectively supply aerodrome lighting data representative of light control characteristics of aerodrome lighting associated with individual aerodromes. The processor is in operable communication with the aerodrome lighting data source and the communication radio, and is configured to selectively retrieve, from the aerodrome lighting data source, aerodrome lighting data associated with an individual aerodrome, and selectively command the communication radio to transmit RF signals consistent with the light control characteristics associated with the individual aerodrome.

Abstract: Methods are provided for presenting procedure information for an airport on a display device onboard an aircraft. A method comprises displaying a map on a display device and displaying a briefing panel overlying a portion the map. The briefing panel includes a plurality of segments, wherein each segment is associated with a type of procedure information for the airport.

Abstract: According to one embodiment, a landing point indication system includes an image provider, a rotorcraft position provider, a pilot image generation system, and a display device. The image provider is operable to provide a visual representation of an area underneath a rotorcraft. The rotorcraft position provider is operable to provide information indicating a position of the rotorcraft. The pilot image generation system is operable to generate a supplemented visual representation. The supplemented visual representation includes the visual representation of the area underneath the aircraft and information indicating a position of the rotorcraft relative to the visual representation. The display device is operable to display the supplemented visual representation within the rotorcraft.

Abstract: The invention relates to a device for assisting in the choice of a diversion airport for an aircraft piloted by a crew (200), said aircraft comprising a flight management system including location means (207) calculating the position of the aircraft, said device comprising a navigation database (202) and a performance database (203) of the aircraft, said device being characterized in that it comprises a company database (201) comprising airports and characteristics of said airports, means (205) of calculating a list of airports, called candidate airports, from the airports in the company database, from the navigation database and from the selected characteristics by the crew, means (204) for calculating remaining flight time and fuel consumption predictions for each of the candidate airports from the position of the aircraft, from weather conditions and from the performance database, and an interface giving the favored airports for diversion according to pre-established criteria or determined in real time usi

Abstract: A method of controlling the flight of a rotorcraft in a feed-forward/feedback architecture includes utilizing an aircraft plant model to control the rotorcraft performance; determining when an external load is coupled to the rotorcraft; and modifying an inverse plant when the external load is present.

Abstract: A taxi method for an aircraft having a primary thrust engine taxi system and an electric taxi system is provided. The method involves obtaining aircraft and airport status data and generating therefrom taxi drive information indicative of the relative cost of taxiing the aircraft along a predetermined route using the electric taxi system versus the aircraft engine taxi system. The taxi drive index information is presented to a user.

Abstract: Systems and methods for monitoring navigation state errors are provided. In this regard, a representative system, among others, includes a receiver that is configured to receive GPS signals and calculate pseudorange (PR) residuals, the receiver including a navigation state error manager that is configured to: calculate a distance traveled by the receiver having the PR residuals, determine whether a navigation state has errors based on the calculated PR residuals and calculated distance, and responsive to determining that the navigation state has errors, send an error message indicating that the navigation state has errors.

Abstract: A device for aiding the following of an airport route by an aircraft includes: an onboard system of optical sensors; means providing the current position of the aircraft; a database having topological information for the airport; a recognition system providing, on the basis of the video images arising from the system of optical sensors, data characteristics of the airport route portion, making it possible to identify a simple primitive representative of the route portion followed; and a processing computer. The processing computer extracts, from the database, a succession of simple geometric shapes representing the airport route and of the same nature as the primitives arising from the recognition system, compares the succession of shapes with the primitives, and validates or invalidates the route followed by the aircraft as a function of the result of the comparison.

Abstract: A flight control system for a flying object comprises a flying object, a navigating means provided in the flying object, a position measuring unit 17, a flight control unit 18 for controlling the navigating means, and a main arithmetic control unit 19 for controlling the position measuring unit and the flight control unit, and in the flight control system for a flying object, the position measuring unit has a GPS device 23 for measuring a ground coordinate of the flying object and a vertical camera 13 for taking a digital image below the flying object and measures an altitude of the flying object based on images at two points taken by the vertical camera, on ground coordinates of the two points measured by the GPS device, and on a focal length of the vertical camera, and the main arithmetic control unit controls the navigating means via the flight control unit based on the measured altitude and makes the flying object fly at a predetermined altitude.

Abstract: A system is provided for controlling the speed of an aircraft with a speed brake during flight. The system includes a guidance system configured to determine a target speed for the aircraft; a speed brake control system coupled to the guidance system and configured to compare the target speed to a current speed to generate speed brake guidance; and a display unit coupled to the speed brake control system and configured to display a visual representation of the speed brake guidance to a pilot of the aircraft.

Abstract: A method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. The method comprises the steps of (1) on the basis of a yaw rate setpoint {dot over (?)}c, determining a wheel-steering prepositioning angle ?p; and (2) using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle ?c equal to the sum of this prepositioning angle ?p and of an angle ?z which is determined taking account of an error between the yaw rate setpoint {dot over (?)}c and the measured yaw rate {dot over (?)}m when the steerable bottom part is steered by the steering angle ?c.

Abstract: A target vertical speed, to be applied to the aircraft upon the initiation of the aircraft's flaring phase, is defined in relation to the ground. An optimized ground slope associated with an approach path to be tracked during the landing, is then determined as a function of the determined target vertical speed and of at least one outside parameter. This optimized ground slope is at least equal to a predefined ground slope. Upon interception by the aircraft with the approach path, the aircraft is guided to track the determined optimized ground slope associated with the approach path and reach the target vertical speed upon initiation of the flaring phase.

Abstract: A method of managing a flight procedure of an aircraft flight plan, which has at least one segment, includes a step in which an additional attribute of the segment representative of a compulsory or optional nature of the flight of said segment is dynamically selected.

Abstract: A method for creating a digital elevation map (“DEM”) from frames of flash LIDAR data includes generating a first distance Ri from a first detector i to a first point on a surface Si. After defining a map with a mesh ? having cells k, a first array S(k), a second array M(k), and a third array D(k) are initialized. The first array corresponds to the surface, the second array corresponds to the elevation map, and the third array D(k) receives an output for the DEM. The surface is projected onto the mesh ?, so that a second distance Rk from a second point on the mesh ? to the detector can be found. From this, a height may be calculated, which permits the generation of a digital elevation map. Also, using sequential frames of flash LIDAR data, vehicle control is possible using an offset between successive frames.

Abstract: A method includes accessing a plurality of acceleration values generated by an inertial measurement unit of an optical system. The method includes identifying a maximum acceleration value (the accessed acceleration value having the greatest absolute value), identifying one or more adjacent acceleration values (the accessed acceleration value adjacent in time to the maximum acceleration value), and identifying a nearest adjacent acceleration value (the adjacent acceleration value having the value nearest the maximum acceleration value). The method includes determining a corrected peak acceleration. The corrected peak acceleration is the sum of a first value corresponding to an average of the maximum acceleration value and the nearest adjacent acceleration value and a second value corresponding to the product of a correction value and the difference between the maximum acceleration value and the nearest adjacent acceleration value.

Abstract: A method for presenting the current drift values of an aircraft on a display device in which the drift values are presented in a vector presentation. The length of the drift vector above a predefined threshold value is presented in a manner proportional to the current drift velocity, and the length of the drift vector below the threshold value is presented in a manner disproportionate to the current drift velocity. There is a continuous transition between the two ways of presentation at the threshold value.

Abstract: Altitude control of a toy flying vehicle intended for indoor hovering flight comprises providing a selected altitude level for the vehicle. A position control signal is transmitted from the vehicle towards a surface. A receiver in the vehicle receives the signal reflected from the surface. A level of the reflected signal by the receiver is determined, and a change of the reflected signal is an indicator of a change of altitude of the vehicle relative to the selected altitude level. The vehicle receiver communicates with the remote controller, and the remote controller can adjust and control speed and direction of the vehicle. Controlling the altitude can be by a stop control; an up and/or down control; and/or a high and/or low height sensitivity control, take-off/landing control; gesture mode control; left/right trim control; control between altitude control mode and manual control mode.

Abstract: The present invention relates to a method for replacing legs in an air navigation procedure described as a series of legs, the legs forming part of an initial family of legs. The method includes: a step of determining a restricted family of legs included in the initial family of legs, so that each leg not belonging to the restricted family corresponds to a combination of legs belonging to the restricted family: The method also includes: a step of replacing in the navigation procedure the legs not belonging to the restricted family with combinations of legs belonging to the restricted family.

Abstract: An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane's angular deviations from the runway centerline and from the glide slope with onboard equipment and then compares those angular deviations to the ILS angular deviation information.

Abstract: The invention provides an automatic taking-off and landing system, comprising a flying object and a taking-off and landing target, wherein the flying object has an image pickup device 21 for taking images found in downward direction, navigation means 4, 5, 6, 8, 9, 10 and 11, and a control unit for processing images acquired by the image pickup device and for controlling the navigation means, and wherein the control unit calculates a positional relation between the taking-off and landing target and the flying object based on the image of the taking-off and landing target as acquired by the image pickup device and controls taking-off and landing operations of the flying object based on a result of the calculation.

Abstract: The present invention applies model-based processing to a sensor output from a sensor such as a sonar, radar, or laser range finder. In particular, embodiments of the invention use a priori knowledge of a model signal return expected from a particular object to identify the location of the object relative to the sensor (and/or vice versa). In some embodiments the object is augmented with reflectors that return the sensor signal back towards the sensor so that the object can be more easily detected by the sensor. In preferred embodiments the reflectors are arranged in an a priori known pattern on the object, to help identify both the location and the orientation of the object with respect to the sensor. In the preferred embodiment, the sensor is a sonar, mounted on an unmanned underwater vehicle (UUV).