Abstract: A method for displaying a runway incursion for an aircraft includes electronically gathering traffic information data from a traffic information system, employing a runway incursion algorithm to the traffic information data to detect a collision hazard, automatically calculating incursion data, and displaying the incursion data. A runway incursion detection system has a display unit, a computer and a software product that enables methodology herein.

Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.

Abstract: A method for checking takeoff or landing parameters of an aircraft including a step of determining takeoff or landing parameters on the basis of a series of input conditions. The method includes steps of calculating regulatory data on the basis of determined takeoff or landing parameters; and of comparing the calculated regulatory data with predefined threshold values, with a view to establishing whether the determined takeoff or landing parameters are valid or invalid.

Abstract: A system and method to facilitate approach of a VTOL aircraft to an offshore facility includes inputting a waypoint for a landing platform of an offshore facility into an aircraft module, inputting an offset distance from the landing platform into the aircraft module, inputting a minimum descent height into an aircraft module, and inputting a final approach inbound course toward the landing platform into the aircraft module.

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: An aircraft (160) approaches a landing point (162) following a flight path (164) to a designation point (166), the pilot sights the landing point (162) and activates the apparatus. A first calculation of coordinates for the landing point (162) is made and landing symbology generated. The pilot reviews the landing symbology and decides whether or not there is an acceptable correlation with (10) the landing point (162). If not, the pilot will continue along the flight path (164) activating the apparatus at further designation points (168, 170 and 172) to reduce the designation error between the coordinates calculated by the apparatus and the real world landing position (162) observed by the pilot until the pilot is satisfied. At this point the pilot enters a landing phase and the (15) symbology provides the pilot with landing cues even when the helicopter (160) enters a brown out event indicated by cloud (174).

Abstract: A proximity detector, unmanned aerial vehicle (UAV), and method for outputting a displacement are provided. The proximity detector includes a velocity sensor, a displacement sensor, and integration logic. The integration login is configured to receive displacement values from the displacement sensor and integrate velocity values received from the velocity sensor. Based on the integrated velocity value and a first displacement value, the integration logic determines an estimated displacement value. A difference is determined between the estimated displacement value and a second displacement value. If the difference is less than a difference threshold, the second displacement value is output. The UAV and/or other vehicles may utilize the proximity sensor to provide data for vehicle control and operation, including maneuvering and landing the vehicle.

Abstract: In exemplary embodiments, braking of an airplane is controlled during a rejected takeoff. A rejected takeoff of an airplane from a runway is initiated. Position of the airplane is determined, such as by inputting aircraft position from a global positioning system. Distance remaining on the runway is determined. Deceleration to stop the aircraft in the determined distance remaining on the runway is calculated, and the calculated deceleration is provided to an autobraking system of the airplane. When the aircraft can not be stopped in the determined distance remaining on the runway, a predetermined deceleration that correlates to maximum braking may be provided to the aircraft's autobraking system. The calculated deceleration may be provided to the autobraking system until a pilot takes command of the aircraft's brakes or the aircraft has stopped.

Abstract: An apparatus is disclosed for monitoring the load on at least one part of an aircraft landing gear during landing of the aircraft. The apparatus comprises a housing containing a sensor which senses a parameter indicative of the load in the part of the landing gear, a processor which receives signals from the sensor and processes the signals to produce data representative of the parameter measured by the sensor, a battery which provides electrical power to the processor, a memory for storing measurement data from the processor, and a wireless transmitter which is controlled by the processor. The wireless transmitter is arranged to transmit at least some of the measurement data from the processor to a remote device located outside of the housing.

Abstract: An aircraft piloting system may include information sources that provide a position indication relating to the aircraft and information that characterizes a virtual approach axis. An information processing unit processes information emanating from the information sources and includes an assisted approach mode function and a landing aid multimode receiver that implements a precision approach. A user device uses the information provided by the landing aid multimode receiver to support the guidance of the aircraft up to its landing.

Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.

Abstract: 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.

Abstract: Method and system for evaluating and implementing air traffic management tools and approaches for managing and avoiding an air traffic incident before the incident occurs. The invention provides flight plan routing and direct routing or wind optimal routing, using great circle navigation and spherical Earth geometry. The invention provides for aircraft dynamics effects, such as wind effects at each altitude, altitude changes, airspeed changes and aircraft turns to provide predictions of aircraft trajectory (and, optionally, aircraft fuel use). A second system provides several aviation applications using the first system. These applications include conflict detection and resolution, miles-in trail or minutes-in-trail aircraft separation, flight arrival management, flight re-routing, weather prediction and analysis and interpolation of weather variables based upon sparse measurements.

Abstract: A device to assist in an independent piloting of an aircraft at least in a descent phase includes a unit to determine a descent axis which assists a pilot in flying from a safe altitude to a decision height, the descent axis being secured relative to the ground being flown over, and a guidance system to assist in the guiding of the aircraft along said descent axis in a descent phase.

Abstract: Embodiments of methods and systems for providing an automatic strategic offset function are disclosed. In one embodiment, a method for enhancing the collision avoidance capability of an aircraft includes determining a flight plan, determining a boundary for the flight plan, generating a variable offset from the flight plan that is within the boundary, the variable offset including a lateral offset distance, and navigating an aircraft based on the variable offset.

Abstract: An approach guidance method for an airborne mobile platform, for example an aircraft, and associated system. The method includes determining a radius of a capture arc tangential to a glide slope, determining an altitude for tangentially intercepting the capture arc, and guiding the mobile platform to an intercept point on the capture arc. The glide slope is associated with a waypoint, and the radius of the capture arc depends on variable mobile platform speed. The altitude for intercepting the capture arc depends on the radius of the capture arc and on variable flight angle.

Abstract: Systems and methods of the present disclosure are used to determine and display arrival, approach, and departure information on a display device in an aircraft, such as a moving map on a multi-function display. An arrival, approach, and/or departure may be received by a flight computer such that the arrival, approach, and/or departure information may be determined based on related approach procedures. Adjustments to navigational instruments may also be made. A pilot may then use the arrival, approach, and/or departure information to safely fly the arrival, approach and/or departure.

Abstract: A method to assist the piloting of an aircraft in a non-precision approach during a landing phase may include a series of successive steps that are carried out interactively and automatically. The steps include verifying, in accordance with respective standards of operation, conditions relating to the correct functioning of a plurality of equipment of the aircraft and to the integrity and precision of measurements of parameters used for implementing the non-precision approach, based on information from the plurality of equipment. On the basis of the verified conditions, an appropriate approach category is selected and presented on a display screen.

Abstract: An imaging system for a rotary aircraft having a millimeter wave imager with visible or infrared overlay. The system includes an active millimeter wave imaging system comprising a millimeter wave transmitter and a millimeter wave phased array receiver for producing millimeter wave images of a landing region, a second imaging system operating at visible or infrared wavelengths to produce visible or infrared images of the landing region, and a processor programmed with a see and remember algorithm for overlaying the visible or infrared images and the millimeter wave images and to save at least one good high-resolution visible or infrared image in case of a brownout event begins to obscuring the visible or infrared images wherein in case of the brownout event the millimeter wave images are overlaid on the at least one good visible or infrared image and not obscured visible or infrared images.

Abstract: A display system for an aircraft includes a processing unit configured to determine a touchdown point for the aircraft and to supply display commands associated with the touchdown point; and a display device coupled the processing unit and configured to receive the display commands and operable to render symbology representing the touchdown point.

Abstract: A routing tool is disclosed. In one embodiment, the method and system include receiving flight data and geographic data in the aircraft, and generating route data based on the flight data and the geographic data. The route data provides information about attainable landing areas for the aircraft.

Abstract: The general field of the invention is that of synthetic vision system SVS type viewing systems, for aircraft, said system comprising at least one navigation database, a cartographic database of a terrain, position sensors, anemometric sensors, sensors for measuring the gradient of said terrain, an electronic computer, a man-machine interface means and a display screen, the computer comprising means of processing the various information obtained from the databases, from the sensors and from the interface means, said processing means arranged so as to provide on the display screen a synthetic image of the terrain comprising a representation of the final destination in the form of an air sock of aeronautical type.

Abstract: Disclosed herein are a system for automatically landing an aircraft using image signals and a method of controlling the system. The system includes an altimeter installed on the aircraft; a landing mark placed at a landing location on a landing runway; a camera installed on the aircraft, oriented toward the front of the aircraft, and configured to detect the shape of the landing mark in image information form; and a FCC configured to calculate the angle between the aircraft and the ground, the ground range and the slant range between the aircraft and the landing location using the altitude information measured by the altimeter, the image information of the landing mark captured by the camera, angle information composed of the pitch, roll and yaw angles of the aircraft, and the angle of entry into the landing runway, and configured to control the automatic landing of the aircraft.

Abstract: The invention relates to a method for assisting the piloting of an aircraft in the vicinity of a landing or takeoff point, by: determining the locus of entry and/or exit points for a given approach and/or departure altitude that are not safe for reaching the landing and/or takeoff point; and presenting a diagram including said locus on a display device.

Abstract: The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.

Abstract: The invention involves a method comprising the steps of providing (S3) a wind data set (3) including wind data of a plurality of positions, receiving (S4) data for a predicted airplane trajectory (311), providing (S5), based on the wind data set (3), a set of wind data elements (302), each including data concerning wind at a position along the predicted airplane trajectory (311), repeating steps of selecting a subset of wind data elements (302S), creating a wind profile (303), and comparing the wind profile (303) to the set of wind data elements (302), and selecting (S10) to be sent to a subscriber (2, 4) a subset of wind data elements (302S) based at least partly on which a wind profile (303) was created corresponding to the largest extent to the set of wind data elements (302).

Abstract: A system is provided for monitoring an energy height of an aircraft during landing. The system includes a database including landing distance data; a processing unit configured to receive the landing distance data from the database and to calculate a landing distance of the aircraft based on a velocity and a height of the aircraft, the processing unit further configured to provide display signals based on the landing distance; and a visual display coupled to the processing unit and configured to provide a visual image based on the display signals.

Abstract: An aircraft synthetic vision system (100) is provided for increasing data input to a pilot (109) during approach and landing flight operations, and includes a runway assistance landing system (114) and a plurality of databases (106, 108, 110, 112) which may include, for example, a terrain database (106), an obstacle database (112); and a validated runway database (110). The processor (104) detects the likelihood of an error in determining the altitude from at least one of the runway assistance landing system (114), the plurality of databases (106, 108, 110, 112), and identifies the error. The processor (104) further determines augmented coordinates, and a processor (104) generates symbology commands to a first display (116) for displaying a runway environment in response to data provided to the processor (104) from each of the runway assistance landing system (114), the plurality of databases (106, 108, 110, 112), and the processor (104).

Abstract: A display system is provided for a vehicle. The system includes a processor configured to receive data representative of landing information and navigation and control information and to supply display commands associated with the landing information and navigation and control information; and a display device coupled the processor for receiving the display commands and operable to render a three-dimensional view, including first symbology representing the landing information and second symbology representing the navigation and control information. The second symbology is superimposed on the first symbology.

Abstract: A system for monitoring a liquid level in an aircraft shock strut includes a cylinder having an internal chamber sealed by a piston telescopically movable within the cylinder. The chamber contains a gas and a liquid, and a sensor assembly is provided for monitoring a condition of a level of the liquid in the chamber. The sensor assembly includes at least one probe within the chamber, and a fitting assembly allows one or more leads from the probe to pass through the wall of the strut while maintaining pressure in the chamber. The fitting assembly includes a plug molded to the one or more leads extending from the probe. The fitting assembly also includes a retainer for holding the plug in sealed relationship with a through passage in the strut.

Abstract: An apparatus and method for determining and indicating a distance between a landing small airplane and a landing surface, wherein the distance is no more than approximately twenty-five feet. The apparatus emits signals from opposite sides of the airplane toward the landing surface, receives the signals reflected by the landing surface, and, based on the differences in time between emitting and receiving the signals, determines the distances from the opposite sides of the airplane to the landing surface. The apparatus is further operable to communicate the shorter distance to the pilot so that he can decide when to perform a flare maneuver.

Abstract: A method of automatically determining a landing runway for an aircraft includes the steps of i) determining control points assigned to a landing runway along a landing approach of an airplane; ii) determining the spatial deviation of the airplane from the determined control points; and iii) determining an appropriate landing runway while taking into account the determined spatial deviation.

Abstract: A system for aiding the piloting of an aircraft during a runway approach includes an information source that provides information relating to the aircraft and its environment. A computation unit determines, with the aid of information provided by the information source, an energy reference profile having a trajectory reference profile and a speed reference profile that allows the aircraft to regain a stabilized approach trajectory, if it follows the reference profile. A monitor verifies that the aircraft is following the reference profile. An indicator supplies the pilot with piloting indications for piloting the aircraft so as to follow the reference profile.

Abstract: A system and method for selectively alerting a pilot of an aircraft about distance remaining to the end of a runway. A position of the aircraft is received. A position of a runway is retrieved from a runway database. The retrieved position of the runway is compared to the received position of the aircraft to determine if the aircraft is within an alert envelope relative to the retrieved position of the runway. The position of the runway is subtracted from the position of the aircraft to determine a distance to the distal end of the runway. An alert to the pilot is generated based upon the distance to the distal end of the runway.

Abstract: The system (1) comprises means (3A to 3D) for detecting incapacity of the pilots to control the aircraft, and means (5) for automatically guiding and piloting the aircraft until it lands at an airport, on detection of such an incapacity.

Abstract: A distribution device for a glide guidance component, the distribution device including an array of antenna elements installed on a pylon. The distribution device includes: a first and a second input for receiving a CSB (carrier plus sideband) input signal and an SBO (sideband only) input signal respectively, a plurality of outputs connectable to the array and including a first and a second output for the first and second output signals, respectively; each of said output signals including a CSB component and an SBO component. The array of antenna elements is such as to irradiate an image-less type pattern and the distribution device is such that the outputs have an substantially equal amplitude value for each pair arranged symmetrically around a central point of the array and a phase difference which is identical for the two CSB and SBO components.

Abstract: The invention relates generally to the control and landing of unmanned aerial vehicles. More specifically, the invention relates to systems, methods, devices, and computer readable media for landing unmanned aerial vehicles using sensor input and image processing techniques.

Abstract: An aircraft pilot kneeboard is provided including a bottom member having an inner compartment. A top member is connected to the bottom member by a first axle. Flanges extend outwardly from the bottom member. Straps are attached to the flanges. Springs are located in the flanges for holding writing instruments. The springs have turns distanced less than a diameter of the writing instruments. Clamps are located at lower and upper edges of the top member. A tiltable surface is connected to an upper surface of the second clamp by a second axle. The second axle extends widthwise across the kneeboard. The kneeboard further includes a light emitting diode for lighting a top surface of the top member. The kneeboard further includes an interactive screen attached to the tiltable surface for providing a military moving map and a brownout/obscured landing system.

Abstract: Turret assemblies for small aerial platforms, including unmanned aircraft, and associated methods are disclosed herein. In one embodiment, an aircraft system can include a turret assembly having a payload with a line of sight to a target and a gimbal system carrying the payload. The gimbal system can include (a) a first support coupled to a first actuator to rotate about a first axis, and (b) a second support carried by the first support and coupled to a second actuator to rotate about a second axis generally transverse to the first axis. The payload can be carried by the second support. A housing at least partially surrounds the payload and the gimbal system. The turret assembly can also include a controller configured to direct movement of at least one of the first actuator and the second actuator such that the line of sight is pointed away from a point of impact before the turret assembly contacts the ground or another external structure during landing or capture operations.

Abstract: A method to detect if an aircraft is airborne or on the ground may include detecting at least one of a truck tilt of each main landing gear and a strut compression of each main landing gear. The method may also include detecting the aircraft being airborne or substantially on the ground in response to at least one of the truck tilt of each main landing gear and the strut compression of each main landing gear.

Abstract: A method and system for preventing the control of an aircraft from the cockpit. In an exemplary embodiment, the system could be triggered externally. For example, an air traffic control (ATC) station could determine that the aircraft has deviated from its planned flight path. If personnel at the ATC station decide that the deviation is not attributable to the actions of the authorized flight crew, the personnel can transmit a signal to the aircraft that disables all normal cockpit control of the aircraft. Once normal flight controls are disabled, the aircraft may execute a preprogrammed emergency flight plan via its autopilot system, with or without the use of a flight management system (FMS). The emergency flight plan could cause the aircraft to fly to a sparsely populated area and enter a holding pattern, or it could cause the aircraft to land in a sparsely populated area or at an airport using an autoland system.

Abstract: Systems and methods for advising a flight crew member that an enhanced ground proximity warning system (EGPWS), for example, may continue to provide terrain alerts, cautions, warnings, or the like because an intended landing site for the aircraft is not recognized within a database of airports. An unknown airport advisory is generated and broadcast after the aircraft is in a landing configuration, when the aircraft is greater than a threshold distance from the nearest landing site in the database, but before the terrain alerts are broadcast. The pilot may actuate a “terrain inhibit” selection device after receiving the advisory. The inhibit device may deactivate or mute subsequent alerts generated by the EGPWS during that particular landing sequence.

Abstract: Methods and apparatus are provided for displaying appropriate identifiers on aircraft taxiways on an aircraft flight deck display. Data representative of taxiway segments, in which each taxiway segment at least partially defines the aircraft taxiway, are supplied. At least a portion of the taxiway segments that define the aircraft taxiway are rendered on the flight deck display. The rendered taxiway segments include identified segments and non-identified segments. The identified segments have the identifier associated with the aircraft taxiway rendered thereon. The non-identified segments do not have the identifier associated with the aircraft taxiway rendered thereon.

Abstract: An electrically activated landing gear control system is provided. A processing module of landing gear control system is provided with landing gear control system software that receives data relating to the position of a landing gear lever. Proximity sensors positioned at landing gear and wheel well areas of the aircraft are coupled for communication with the processing module. The proximity sensors provide the landing gear control system software with position data relating to the landing gear. The landing gear control software converts the data received from the landing gear lever and the data received from the proximity sensors to command signals to control electrically activated valves associated with landing gear components. The command signals may be sent simultaneously to remote power distribution units and remote data concentrator units to energize or de-energize solenoid coils of the electrically activated valves.

Abstract: The device (1) comprises means (2) for automatically determining first instructions enabling the aircraft to follow another aircraft with a particular separation, means (3) for automatically determining second instructions making it possible to perform a landing procedure, and means (6, 9) for automatically applying to the aircraft said first instructions or said second instructions according to its energy state.

Abstract: A display system is provided for displaying runway landing data. The system includes a processor and a display device. The processor is adapted to receive data representative of an aircraft landing operation and is operable, in response thereto, to supply one or more image rendering display commands. The display device is coupled to receive the image rendering display commands and is operable, in response thereto, to render an image representative of a runway and a segment of the runway that will be used to land and stop the aircraft during the aircraft landing operation. A method for displaying the runway landing data is also provided.

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: A method for landing an aircraft includes determining the aircraft's deviation from its approach path so as to define a first point of the aircraft's heading. A first straight line passing through the first point and through a second point defining the ground orientation of the approach path is displayed, by a head-up display, on a horizon line with a heading scale. The first straight line represents a ground plot of the approach path. A first assistance gate is displayed such that the first straight line passes through the first assistance gate when the aircraft is aligned on the approach path. A second straight line, parallel with the horizon line and passing through the first point, is displayed and represents a plot on the ground of the origin of the approach path. A second assistance gate is displayed under the horizon line and represents the slope of the approach path.

Abstract: A current path display indicator for a display device of a vehicle. The current path display indicator includes a flight path indicator (FPI) and a visual cue associated with the FPI to indicate relative direction from the vehicle's current path to a desired path. The visual cue may be embodied in possibly a number of different ways. For example, it may be embodied as an arrow extending from a circular portion of the FPI; a highlighted segment superimposed on the circular portion of the FPI; a triangle extending from the circular portion; or, a pie-shaped marker contained within the circular portion.

Abstract: A method, apparatus, and computer program product for detecting anomalies in a landing system. In one embodiment, a magnitude difference between a blended inertial deviation magnitude and a raw deviation magnitude is identified to form a magnitude difference. The magnitude difference is compared to a magnitude threshold. If the magnitude difference exceeds the magnitude threshold, an anomaly in the data is detected.