Abstract: A system for monitoring a vehicle having systems, components, and sensors has a nominal controller and an adaptive controller. A vehicle health function module is coupled to an output of the adaptive controller and generates a vehicle health output signal indicating a prognosis of at least one of the systems or components degradation of the vehicle.

Abstract: A warning light circuitry includes a first logic gate adapted for receiving a first, a second, a third, and a fourth input signal; a second logic gate adapted for receiving a fifth, a sixth, and a seventh input signal; a third logic gate electrically connected to the first and second logic gate; and a warning light electrically connected to the third logic gate. The first logic gate is adapted for providing a first output signal to the third logic gate upon receiving the first, the second, the third, and the fourth input signals. The second logic gate is adapted for providing a second output signal to the third logic gate upon receiving the fifth, the sixth, and the seventh input signals. Therein the third logic gate is adapted for triggering the warning light upon receiving the first or the second output signal.

Abstract: A reverse thrust detent system for an aircraft includes a throttle quadrant having an intermediate reverse thrust detent position, a reverse thrust scheduling system interfacing with the throttle quadrant, at least one aircraft engine interfacing with the reverse thrust scheduling system and a programmable input interfacing with the reverse thrust scheduling system and adapted to receive an engine reverse thrust setting. The reverse thrust scheduling system is adapted to operate the at least one aircraft engine according to the engine reverse thrust setting responsive to actuation of the intermediate reverse thrust detent position of the throttle quadrant. A reverse thrust detent method for an aircraft is also disclosed.

Abstract: Disclosed is a method for the monitoring of a cabin region of a transport system located outside a field of view, wherein at least one light beam is emitted, passing through the cabin region in the longitudinal direction, and in the event of a disturbance of the at least one light beam path a message is generated. A monitoring device is also provided, with at least one emitter unit for purposes of emitting at least one light beam, with at least one receiver unit for purposes of receiving the emitted light beam, and with at least one messaging unit for purposes of generating a message in the event of a disturbance of the at least one light beam path; also disclosed is an aircraft cabin with at least one such monitoring system.

Abstract: A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition.

Abstract: A taxiway approach advisory system. The system may include a computer-readable memory containing runway information and a processor in data communication with the memory. The processor may include a component for ascertaining the altitude of an aircraft, a component for ascertaining the location of the aircraft, a component for accessing runway information from the memory and determining if the aircraft is within a pre-determined runway envelope based on the altitude and location, and a component for issuing an indication if the aircraft is not within the pre-determined runway envelope.

Abstract: A method and apparatus for monitoring an interior of a fuel tank. Information about a fuel level and moisture in the interior of the fuel tank of a platform is generated using a fuel sensor unit in the interior of the fuel tank. The fuel sensor unit comprises a sensor configured to be located in the interior of the fuel tank and generate information about the fuel level in the fuel tank and the moisture in the fuel tank and a wireless unit electrically connected to the sensor. The wireless unit is configured to receive the information from the sensor and transmit the information using wireless signals. A number of actions is identified based on the information about the interior of the fuel tank.

Abstract: A method and apparatus for lighting a flight deck on an aircraft. A status of the aircraft is identified by a processor unit. The processor unit controls the lighting on the flight deck in response to the status of the aircraft to indicate the status of the aircraft.

Abstract: A system and method to display, when within an envelope of an ownship's flight path, a symbol representing wake turbulence from another aircraft based on aircraft type and flight parameters received from the other aircraft, the symbol being formatted to indicate the severity of portions of the wake turbulence. The format is modified periodically in accordance with the aircraft's flight path and a decay rate of the wake turbulence.

Abstract: Systems and methods for performing airport surface collision-avoidance. A wingtip-mounted camera allows the pilot to positively ascertain that the wingtip will clear objects located in the video. An exemplary system implemented on an aircraft includes a wingtip module having a camera that generates a video stream and a communication device that transmits the generated video stream. A processor receives the video stream and generates a reticule for the video stream. A display device simultaneously presents the video stream and the reticule. The reticule includes a horizon line and is based on a focal length of a lens of the camera and height of the camera above ground. The reticule includes curved and/or straight distance lines and curved or straight travel lines. The travel line(s) correspond to at least one aircraft component or a zone of importance and are based on location of the camera and trajectory of the aircraft.

Abstract: A method, apparatus and system for generating an indication of an object within an operating ambit of heavy loading equipment is disclosed. The system includes a plurality of sensors disposed about a periphery of the loading equipment, each being operable to generate a proximity signal in response to detecting an object within a coverage region of the sensor, the proximity signal including an indication of at least an approximate distance between the sensor and the object. A processor circuit is operably configured to define an alert region extending outwardly and encompassing swinging movements of outer extents of the loading equipment. The processor circuit is operably configured to receive proximity signals from the plurality of sensors, process the signals to determine a location of the object relative to the loading equipment, and initiate an alert when the location falls within the alert region.

Abstract: 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.

Abstract: A display device has a holding device wearable on a user's head and holding a multifunctional glass that comprises a first and second coupling-out section and a coupling-in section, an image generation module that generates and couples an image into the multifunctional glass through the coupling-in section to the first coupling-out section redirecting the image in the direction of the user such that the user can perceive the image in superimposition with the real environment, a control unit for the image generation module, and a detector which is connected to the control unit and which measures the intensity of ambient light coupled through the first coupling-out section to the second coupling-out section and coupled out of the multifunctional glass through the second coupling-out section. The control unit controls the brightness of the image of the image generation module, the brightness controlled according to the intensity measured by the detector.

Abstract: Methods and systems are provided for determining over focalization of a pilot of an aircraft. The method includes receiving human parameter data from one or more systems that observe conditions associated with the pilot and receiving controls data that indicates an interaction of the pilot with one or more control systems of the aircraft. The method includes, based on the human parameter data and the controls data, generating at least one alert. The method also includes communicating the at least one alert to the pilot to change a focus of the pilot.

Abstract: A method and an instrumentation system for an aircraft are provided. The method of presenting aircraft information includes activating a master indicator in response to a trigger event associated with operation of the aircraft, receiving a user input associated with the master indicator, and displaying information associated with the trigger event in response to receiving the user input associated with the master indicator. The instrumentation system performs the operations of the method.

Abstract: A method and apparatus for providing assistance to a flight crew during flight. An image of a group of instruments on a flight deck of an aircraft is generated with an image sensor in a data processing system. Assistance information configured to assist the flight crew from flight information displayed by the group of instruments in the image is generated. The assistance information is displayed on a display device in the data processing system.

Abstract: A method to develop a system for management of warnings and electronic procedures for an aircraft, comprising a database of parameters relating to the warnings and to logic and procedures, the aircraft comprising ATA equipment, comprises definition and calculation of maturity criteria for development of the system, which comprises, in order: A) verification of warnings in the database with respect to predefined lists of warnings and calculation of a maturity criterion, B) if the criterion of A>predetermined threshold, verification of the coherence of the logic for the warnings then definition and calculation of a maturity criterion, C) if the criterion of B>predetermined threshold, verification of the existence of the procedures and, for each warning, analysis of its logic with respect to its procedure, then definition and calculation of a maturity criterion, the system being fully set up when the latter criterion>predetermined threshold.

Abstract: A device and a method are provided for outputting items of information regarding a vehicle, in particular regarding a vehicle function. In order to impart the driver an improved knowledge of the vehicle functions, a first storage device, with which the items of information can be retrievably stored, a first device, with which a workload of the driver can be determined, a second device with which an associated priority can be provided to each item of information, and an output device are provided. If the determined workload undershoots a predeterminable limit workload, the item of information with the highest priority is output via the output device. The second device is embodied and equipped in such a manner, that following outputting of an item of information through the output device, the priority of this item of information is reduced.

Abstract: An aircraft interface apparatus for providing communication between an aircraft system and a device for use on an aircraft comprises a first communication means for providing communication with the aircraft system, and a second communication means for providing communication with the device, wherein the aircraft system uses a first data format and the device uses a second data format, and the apparatus further comprises: an interface processing resource that is configured to receive data in a first format from the device and, in response, to output data in the second format to the aircraft system and/or to receive data in the second format from the device and, in response, to output data in the first format to the aircraft system.

Abstract: A taxi guidance system is provided for an aircraft having a primary thrust engine and an onboard electric taxi system. The taxi guidance system includes or cooperates with a source of aircraft status data for the aircraft, and a source of airport feature data associated with synthetic graphical representations of an airport field. The taxi guidance system includes a processor operatively coupled to the source of aircraft status data and to the source of airport feature data to generate, in response to at least the aircraft status data and the airport feature data, taxi path guidance information for the aircraft, start/stop guidance information associated with operation of the primary thrust engine, and speed guidance information for the onboard electric taxi system.

Abstract: An electrically activated latch for aircraft stowage bins includes an overhead stowage bin module having a stationary support structure and a movable stowage bin portion. An electrically operated stowage bin latch mechanism latches the movable stowage bin portion in a closed position and unlatches the movable stowage bin portion to an open position. An electrically operated stowage bin activation switch operates the stowage bin latch mechanism, allowing the aircraft stowage bins to be locked by independently controlling the overhead stowage bins through the aircraft cabin management system, or by control of the latch by the stowage bin activation switch.

Abstract: An optical interrogator system including a broad spectrum light source capable of emitting light having a spectral width spanning at least approximately 20 nm, and at least one optical sensor coupled to the broad spectrum light source by at least one multimode optical fiber, wherein the at least one multimode optical fiber is configured to support a plurality of propagation modes, and a method of using the same are disclosed herein.

Abstract: A terrain warning system includes an indicator to inform a pilot of a proposed degree of flight parameters for safely clearing terrain. An aural message may identify a vertical speed that may be used to safely traverse terrain to the pilot. A visual indicator on a display informs the pilot of a vertical speed or climb angle to traverse terrain. The display may be a vertical speed indicator also capable of displaying traffic advisories.

Abstract: Lighting devices are provided including those which have an array of spatially distributed optoelectronic sources, each source being adapted to emit a respective incident optical beam; a first reflector having an optical axis, and having a first reflective surface that is concave and facing the array of sources to intercept said incident optical beams and to produce corresponding reflected optical beams; a second reflector having a second reflective surface interposed along said optical axis between said array of optoelectronic sources and the first reflector adapted to intercept and deflect said reflected optical beams producing corresponding deflected optical beams, the first reflector being adapted to concentrate the reflected optical beams on the second reflective surface.

Abstract: Present novel and non-trivial methods for presenting taxi information to a pilot are disclosed. Each method may generate an image data set from taxi information data and navigation reference and object data. A first image data set may be representative of an image in which one or more first location highlighter(s) highlighting the location(s) of one or more raised surface feature(s) appears within an egocentric or exocentric three-dimensional representation of a scene located outside the aircraft. A second image data set may be representative of an image in which one or more unconventional surface feature(s) highlighting the location(s) of one or more raised surface feature(s) appears within an egocentric or exocentric three-dimensional representation of a scene located outside the aircraft. A third image data set may be representative of an image in which one or more unconventional surface feature(s) appears within an airport surface map.

Abstract: A method for detecting piloting conflicts between the crew and the autopilot of an aircraft. According to the method, an automatic trajectory is programmed by checking whether the actual values of navigation parameters converge on said corresponding desired values within a predetermined convergence period; in the case where at least one of the actual values does not converge, within the convergence period, on the corresponding desired value, a predictive calculation is carried out, at consecutive future moments, of the value of at least one particular parameter selected amongst the navigation parameters; and in the case where the predicted value of the particular parameter is higher than a corresponding predefined threshold, an alarm is emitted for the crew of the aircraft to notify them about a piloting conflict being able to jeopardize the flight safety of the aircraft. A device for implementing the method. An aircraft including the device.

Abstract: A system and method for assisting flight crew recovery in the aftermath of an unexpected event is provided. A processor is used to detect that an unexpected event has occurred in an aircraft and, in response to detecting that the unexpected event has occurred, state data are stored in memory. The processor is also used to detect that the unexpected event has been resolved and, in response to detecting that the unexpected event has been resolved, the processor retrieves the state data from the memory, generates an aftermath plan that includes prompts to guide the flight crew to complete the aftermath plan, and continuously updates the aftermath plan until the aftermath plan is completed.

Abstract: The invention relates to a device aboard an aircraft comprising output means configured to restore information relating to the aircraft status from aircraft systems, the device including a module providing interface between said output means and said aircraft systems, said module being configured to synthesize information from aircraft systems depending on predetermined behavior rules and to transmit said information thus synthesized to said output means.

Abstract: Method and apparatus for managing equipment on an aircraft. An apparatus comprises an interrogator, a display system, and a processor unit. The interrogator is configured to read information from a set of wireless tags associated with a set of equipment in an aircraft. The processor unit is configured to identify the set of equipment from the information read from the set of wireless tags by the interrogator. The processor unit is further configured to display a layout of an interior of the aircraft on the display system. The processor unit is further configured to display a number of graphical indicators for the set of equipment on the layout in a number of locations on the layout corresponding to a number of locations of where the set of equipment is located in the interior of the aircraft.

Abstract: The present invention relates to a method and system for controlling air traffic. The method and system utilizes aircraft performance data, provided either by an FMS of a capable aircraft or generated by a model based on knowledge of the aircraft, to provide an accurate prediction of aircraft intent so that an accurate estimated time of arrival can be generated. The estimated time of arrival is then used to provide a required time of arrival (RTA) for the aircraft. The RTAs for the aircraft are provided for the aircraft to arrive at a destination, such as an Outer Fix Point, in a desired sequence. The desired sequence is arranged to provide intervals between the aircraft such that they may be able to land at the destination airport without requiring holding and vectoring from top of descent.

Abstract: The invention relates to an alarm apparatus (1) for a pilot's headset (3) and to a pilot's headset having such an alarm apparatus. The alarm apparatus comprises an attitude sensor (11), which detects its inclination relative to a starting position or the horizontal, and a measuring device (12) for recording a period for which the inclination recorded by the attitude sensor exceeds a stipulated inclination tolerance limit. In addition, the alarm apparatus has a means (13) which is set up to trigger an alarm signal when a recorded period of the inclination tolerance limit being exceeded is longer than a preset maximum period.

Abstract: A method and apparatus for displaying aircraft information. A selection of a piece of dynamic information is detected about an aircraft on a first display on a user interface. The piece of dynamic information is used to operate the aircraft and changes during operation of the aircraft. The piece of dynamic information selected from the first display is added to a custom display on the user interface. The custom display is displayed on the user interface on a display system for the aircraft.

Abstract: Methods and apparatus for enabling an air traffic control system to set a beacon code on a transponder of an aircraft without voice communication with the flight crew. In one embodiment, an air traffic control system receives a flight plan from an aircraft, relays clearance of the flight plan to the aircraft, sets a beacon code on a transponder on the aircraft without voice communication, receives an acknowledgement of the beacon code setting from the aircraft, sends an acknowledgement to the aircraft, sets a new beacon code on the transponder without voice communication and receives a new acknowledgement of the new beacon code from the aircraft.

Abstract: A method is provided for inferring the aircraft intent of an aircraft from an observed trajectory. Aircraft performance data relating to that type of aircraft is retrieved from memory, along with atmospheric conditions along the observed trajectory. An initial set of candidate aircraft intents is generated. Each aircraft intent provides an unambiguous description of how the aircraft may be flown that allows a determination of an unambiguous resulting trajectory. A computer system calculates a trajectory defined by each candidate aircraft intent and forms a cost function from a comparison of each calculated trajectory to the observed trajectory. An evolutionary algorithm evolves the initial candidate aircraft intents, wherein the evolutionary algorithm uses a multi-objective cost function to obtain a cost function value that measures the suitability of each candidate aircraft intent.

Abstract: Present novel and non-trivial system, device, and method for combining image data received from two or more vision systems are disclosed. A system may be comprised of a first vision source, a second vision source, and an image generator (“IG”). The first vision source may be could configured to generate a first image data set and a depth buffer data set, and the second vision data source could configured to generate a second image data set. The IG could be configured to receive both the first and second image data sets; the depth buffer data set; and generate a third image data set as a function of both image data sets, the depth buffer data set, and a pixel cutoff distance that may be fixed or variable. In addition, the pixel cutoff distance may be determined as a function of input variable data.

Abstract: Present novel and non-trivial system, device, and method for varying the visibility of symbols depicted in a vertical situation display (“VSD”). An image generator receives zone data and defines a plurality of zones, where the zone data is comprised of second image data representative of a non-VSD zone symbol(s) or feature data representative of a zone feature(s). First image data representative of a VSD is generated, where the VSD is comprised of at least one VSD symbol representative of a zone symbol or a zone feature located in one of the three zones. If the represented zone symbol or zone feature of a VSD symbol is located within a left zone or a right zone, the visibility of each VSD symbol is variable and dependent of its proximity to a center zone.

Abstract: A mass notification push application and a civic-communication application combined into one with the primary purpose of allowing up-to-the-minute UAV aerial imagery as selected by drone ground-based commanders to be automatically transmitted to subscribed end-users via the current OS mobile operating systems for smartphones, iPads, laptops, and web-enabled devices in a manner comprised of separate technologies such as voice (voice to text, voice recognition), video stills (embedded with personalized iconographic identifiers), and with a secondary purpose of allowing the notified recipients to engage others by allowing the retransmitting of received messages along with (or without) registered user annotations so as to create a civil communications hub for wider, real-time dissemination of ongoing situational awareness data.

Abstract: Methods, systems, and computer-readable storage media provide for selective Notice to Airmen (NOTAM) notifications to be made to the crew of an aircraft according to the relevance of the NOTAM to a selected phase of flight of the aircraft. According to embodiments described herein, NOTAMs are received and parsed for subject and status codes. The subject and status codes are used with the selected phase of flight to determine a relevance code each NOTAM according to a set of relevance rules. The relevance rules provide a level of relevance of the NOTAM to the phase of flight and trigger a type of notification according to that level of relevance.

Abstract: A method, apparatus, and computer program product for identifying wireless devices. Information is received from a wireless device that is unidentified. An object associated with the wireless device is identified using a number of types of information in the information and the information.

Abstract: A method for alerting a user of a sequence of events that has occurred, based on data contained within messages occurring on one or more communications buses is described. The method includes entering, via a user interface, data defining a sequence of events for which an alert is desired, monitoring, with a unit coupled to the user interface, the messages occurring on the one or more communications buses for data indicative of an occurrence of the defined sequence of events, and providing an indication to the user that the sequence of events has occurred.

Abstract: Systems and methods to mitigate instrument landing system (ILS) overflight interference are disclosed. An example method performing a first measurement of a position of an aircraft relative to a first location based on an instrument landing system, performing a second measurement of the position of the aircraft based on inertial measurements performed over a first time period occurring prior to the first measurement, performing a third measurement of the position of the aircraft based on inertial measurements performed over a second time period greater than the first time period and occurring prior to the first measurement, and generating guidance information based on a selected one of the first, second, or third measurements of the position of the aircraft.

Abstract: Systems and methods are operable to present braking distance information to crew of an installation aircraft. An exemplary embodiment determines a braking distance for a braking maneuver of the installation aircraft, wherein the braking distance is based on a current ground speed of the aircraft; and generates a graphical representation that is presented on a display, wherein a location of a graphical icon on the graphical representation indicates the determined braking distance from the installation aircraft.

Abstract: A method and apparatus for displaying information is presented. The information is sent from a number of sources to a display unit. The information is displayed through pixels located in the display unit. Heat is transferred in the display unit through a conductive path.

Abstract: A cockpit display system for a cockpit of an aircraft includes a primary flight display moveably located in the cockpit and viewable from a pilot position and/or a copilot position in the cockpit. The primary flight display is movable from a first position utilized for a first operating condition of the aircraft to a second position to increase external visibility during a second operating condition of the aircraft. A cockpit system includes a pilot operating position and a first flight display moveably located in the cockpit and viewable from the pilot operating position. The first flight display is movable from a first position utilized during a first operating condition of the aircraft to a second position to increase external visibility from the pilot operating position during a second operating condition of the aircraft.

Abstract: An alerts and procedures management system for an aircraft comprises a software kernel aboard the aircraft and a parameterization tool for the software kernel, which comprises a conversion module for converting a configuration file describing an operational need of the system into a database of binary parameters which is able to parameterize the software kernel. The software kernel comprises at least four elementary cells: a first cell for acquiring aircraft signals, a second cell for characterizing state variables of the aircraft, a third cell for computing at least one separate event, a fourth cell for scheduling the separate events for communication with the crew; each of the cells comprising a software engine parameterizable by the database.

Abstract: A method for displaying information by means of a dual-view-display in a passenger-cabin of an air-/spacecraft, comprising the following steps: providing the dual-view-display on a predetermined portion of the passenger-cabin; providing first information by means of the dual-view-display, in such a way that said information can be perceived from a gangway between rows of seats of the passenger cabin; and simultaneously providing second information, different from the first information, by means of the dual-view-display, in such a way that said information can be perceived from one of the rows of seats. A display device for displaying information in a passenger-cabin of an air-/spacecraft, comprising a dual-view-display which is arranged on a predetermined portion of the passenger-cabin, the dual-view-display being configured to provide first and second information in the above described ways. A passenger-cabin for an air-/spacecraft comprising said display-device.

Abstract: A display module for displaying passenger-specific display information in an aircraft, comprising: a display, a control unit, a storage device, and a first interface, wherein the first interface is connected to the control unit, and wherein the control unit is designed, on the basis of a signal that is present at the first interface, to read out a storage device content stored in the storage device and associated with the signal in relation to display information, and on the basis of the read-out storage device content and of the signal present at the interface to control the display.

Abstract: An instrument panel for a rotorcraft having two pilot seats, said instrument panel being arranged under an anti-glare shield (4) and including display means (2), at least some of the display means (2) being suitable for acting as communications means, said display means (2) comprising a first set (5) of display means (2) arranged on the instrument panel, and a second set (6) of display means (2) arranged on the instrument panel, wherein the instrument panel includes, symmetrically relative to a longitudinal axis, a central dashboard (3), and at least two lateral dashboards arranged on either side of the central dashboard (3), the dashboards being mutually parallel and presenting a forward longitudinal offset from one dashboard to the next starting from the central dashboard (3).

Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a calculation step for converting an angular deviation into an equivalent linear deviation, and, conversely, converting a linear deviation into an equivalent angular deviation. The method comprises a step of graphic representation, called unified monitoring, intended for the crew, of a deviation of the aircraft, on a lateral deviation axis and a vertical deviation axis; each of the deviations, lateral and vertical, being able to be represented on a linear scale, an angular scale or a mixed scale.

Abstract: A system and method monitor aircraft state parameters, for example, aircraft movement and flight parameters, applies those inputs to a spatial disorientation model, and makes a prediction of when pilot may become spatially disoriented. Once the system predicts a potentially disoriented pilot, the sensitivity for alerting the pilot to conditions exceeding a threshold can be increased and allow for an earlier alert to mitigate the possibility of an incorrect control input.