Abstract: A method and apparatus for operating an aircraft. An aircraft system comprises a housing, a standby aircraft management system, and a backup power system. The standby aircraft management system is associated with the housing and is configured to provide communications, navigation, and control of a number of aircraft systems needed for safe flight and landing of an aircraft in which the standby aircraft management system is located. The backup power system is configured to supply power to the standby aircraft management system when the power is unavailable from the aircraft.

Abstract: A graphical in-flight message representation system comprises a sensor configured to measure a characteristic of a flight of an aircraft and a communication device configured to send and receive in-flight messages. An in-flight message is a message communicated during the flight of the aircraft. The system also comprises a display unit configured to display a graphical flight progress indicator and one or more message icons, each of the one or more message icons corresponding to a respective in-flight message. The graphical flight progress indicator is representative of the characteristic of the flight measured by the sensor. Each of the one or more message icons are displayed in location relative to the graphical flight progress indicator based on the measured characteristic of the flight when the respective in-flight message was communicated.

Abstract: Systems and methods are disclosed for displaying the current trends (i.e., turning or going straight) or the future positions of vehicles of interest on a traffic display unit. The position, orientation and geometry of the displayed symbology is a function of parametric information broadcast by the vehicles of interest and processed by a computer system that controls the traffic display unit. In particular examples disclosed herein, the traffic display unit is a navigation display on an aircraft or a traffic display unit at a traffic controller's station. However, the methods disclosed herein have application to vehicular traffic other than aircraft, such as boats or ships.

Abstract: An aircraft display system is provided and configured to render a cockpit display having a field-of-view. The system comprises a monitor and a processor coupled to the monitor and configured to generate a vertical situation display on the monitor. The vertical situation display includes at least one graphic indicative of a region of the terrain encompassed by the field-of-view.

Abstract: Present novel and non-trivial systems and methods for positioning a heading-based image within a track-based image and for generating steering commands for a forward-looking image capture device of an enhanced vision system (“EVS”). The positioning system is comprised of a source of navigation data, a source of first image data representative of a track-based image, a source of second image data representative of a heading-based image, and an avionics system processor (“ASP”) configured to receive the navigation data, the first image data, and the second image data, determine image positioning data, and merge the first image data with the second image data as a function of the image positioning data. The steering commands generating system is comprised of a source of navigation data, the ASP configured to generate steering command data commensurate to a wind correction angle, and the EVS configured to receive the steering data.

Abstract: A system and method provide situational awareness for a pilot of an ownship in managing the longitudinal interval from an aircraft from which the ownship is following and maintaining the ownship within performance limits by displaying an airspeed bar containing markers representing the ownship minimum and maximum airspeeds, the ownship indicated airspeed, and a commanded interval management airspeed (CIMS) for providing speed situational awareness. A flight management system modifies the CIMS in response to a distance between the aircraft and the ownship. An optional pointer attached to the marker representing the CIMS indicates a trend in the in the CIMS.

Abstract: A system for validating ground determination of gross weight of aircraft includes sensor(s) that generates information regarding ground determination of gross weight while parked at parking bay; processing device that receives information regarding ground determination of gross weight of the aircraft from sensor(s); and computer memory communicatively coupled to processing device. Processing device determines ground determination based on information regarding ground determination of gross weight generated by sensor. Processing device determines gross weight in air after takeoff based on indicated airspeed, angle of attack, and thrust applied to aircraft. Processing device determines error between ground determination and air determination of gross weight taking into account reduction in gross weight due to fuel consumed since receiving ground determination. Processing device updates information regarding relationship between ground determination and air determination of gross weight.

Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.

Abstract: A method and apparatus for managing a touch screen system. Data generated by an acceleration detector about acceleration of the touch screen system is received. The acceleration detector is located within the touch screen system. An action is initiated by an input manager when the acceleration of the touch screen system reduces usability of the touch screen system.

Abstract: A method for estimating airspeed of an aircraft includes receiving values indicative of operating conditions of the aircraft along an axis; estimating a tip path plane (TPP) angle along the axis from at least one of the operating conditions to create an estimated TPP angle; and determining an estimated airspeed as a function of the estimated TPP angle, the determining including referencing a look-up table that indexes the estimated TPP angle with the airspeed.

Abstract: Systems and methods are operable to present graphical information indicating capability of an aircraft to change altitude. An exemplary embodiment determines an altitude change capability of the aircraft; determines an altitude change capability icon based on the determined altitude change capability of the aircraft, wherein the altitude change capability icon is defined by at least a leading portion, a trailing portion, a top portion, and a bottom portion, wherein a slope of the leading portion of the altitude change capability icon corresponds to the determined altitude change capability of the aircraft, and wherein the leading portion and the trailing portion are separated by at least the top portion and the bottom portion; and communicates the altitude change capability icon to a display for presentation to the crew of the aircraft.

Abstract: The dialog device includes a display screen, on which are displayed three graphic representations, which are respectively associated with the three control axes of the aircraft, each of said graphic representations comprising a plurality of portions, each of which is associated with a guidance mode of the associated control axis, so that all the possible guidance modes of the guidance system are thus represented, this representation highlighting the fact that the guidance modes are active exclusively on a given guidance axis.

Abstract: According to one embodiment, an integrated aircraft trim assembly features a shaft, a mechanical stop, a trim motor, a clutch, and a measurement device. The mechanical stop device is operable to at least partially prevent rotation of the shaft outside of an allowable range of motion. The trim motor has an output component in mechanical communication with the shaft. The clutch separates the trim motor from the shaft. The measurement device is proximate to the shaft and operable to measure a position of the shaft and communicate the measured position to a flight control computer operable to change a position of a flight control device.

Abstract: The vertical profile management device includes a flight management system unit that selects a plurality of successive standard cruise sections, each comprising a level phase and a transition phase. The cruise sections are defined by a plurality of features, including waypoints corresponding to a section starting point and a section ending point, a transition type, a transition mode, a transition speed, a level altitude, and a level speed. The flight management system unit also joins together the successive cruise sections in order to form a vertical profile of a flight plan. The cruise sections are configured to be added, removed, or re-sequenced in the flight plan because each section ending point is configured to be the section starting point of a next cruise section in the series.

Abstract: A method and apparatus for providing broadband signals to a portable user device is disclosed. Broadband signals, such as satellite radio signals, are received at a base station having a plurality of antennas. The content of the broadband signals are then encoded using space time coding (STC), and the STC encoded broadband content is transmitted from the plurality of antennas via a first wireless network protocol. The STC encoded broadband content can be received at a portable user device having a plurality of antennas or at a wireless access point having a plurality of antennas, which then transmit the broadband signals via a second wireless network protocol.

Abstract: The invention relates to a method of assisting piloting an aircraft. The method is performed when the real position of a symbol for display lies outside the display limit of the screen. The symbol is representative of a parameter associated with the dynamic behavior of the aircraft (FPV, . . . ) or liable to influence said behavior (FD, . . . ). The symbol possesses two components, and the first component is to be given precedence on display over the second component. In the method, the display of the symbol depends firstly on the orthogonal projection (FPV-lock) of the real position (FPV) of the symbol onto the axis of the first component, and secondly on the position of said projection relative to the display limit of the screen. Such a display makes it possible to give reliable information to the pilot.

Abstract: A method and apparatus for managing a map of an airport. The map of the airport is displayed on a display device. A movement of a number of fingers with respect to a number of aeronautical objects on the map of the airport is detected. Information generated by an operation based on the number of aeronautical objects on the map of the airport is displayed in response to detecting the movement of the number of fingers with respect to the number of aeronautical objects on the map of the airport.

Abstract: Disclosed herein is a three-dimensional (3D) digital map system for implementing a navigation and ground collision preventing method using 3D terrain information. The 3D digital map system includes a terrain referenced navigation module configured to receive data from EGI (Embedded GPS/INS), a radio-altimeter (RALT) and a map database, corrects the data to perform accurate navigation computation, and outputs the corrected data, a collision avoidance warning module configured to generate a warning against collision of an aircraft with the ground or an obstacle using the corrected data, a 3D terrain database and an obstacle database, a terrain following module configured to generate a terrain following trajectory of the aircraft using the same information, and a Passive Ranging module configured to receive the 3D terrain database and line-of-sight (LOS) information of a target and calculate distance and position information of the target located on the ground.

Abstract: The disclosed embodiments relate to methods and systems for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and/or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition.

Abstract: The system according to the invention comprises a display and a synthetic image dynamic generating assembly. It includes a management assembly for the graphic interface of the display, capable of controlling the dynamic display, on a first region of the display, of a synthetic image and able to maintain, in certain movement configurations of the aircraft, a second region of the display delimited by the edge substantially with no synthetic surface representation of the terrain. The management assembly includes means for dynamically delimiting the edge of the first region. The delimiting means are configured to dynamically compute the position of the edge as a function of a determined visibility distance (DV), taken relative to the aircraft.

Abstract: Methods and apparatus for assessing threats to a vehicle to facilitate a reflexive response. Threat timeline parameters for a detected threat to the vehicle including a threat mode and a time progression of the threat in the threat mode is determined based, at least in part, on a plurality of information sources. One or more candidate solutions for facilitating the reflexive response to the threat are determined based, at least in part, on the threat mode and the time progression and one or more of the candidate solutions are presented to an operator of the vehicle to enable the operator to mediate the threat.

Abstract: A flight information system may include a plan vertical situation display. The plan vertical situation display may display a vertical view of a flight path of an aircraft. The plan vertical situation display may display at least one path symbol showing at least one of a current path of the aircraft, a modified but not executed route of the aircraft, and an inactive route of the aircraft. The at least one path symbol may be adapted to display each of the current path of the aircraft, the modified but not executed route of the aircraft, and the inactive route of the aircraft. The plan vertical situation display may further display at least one terrain symbol showing a vertical terrain in the flight path along the at least one path symbol.

Abstract: The system includes additional display means including at least one additional screen and additional graphic interface handling means of the additional screen (able to display on the additional screen, a summary window depending on the operational state of the aircraft. The summary window comprises at least one first pictogram able to be displayed on a first display window of main display means of the aircraft without being displayed on the second window of the main display means, and at least one second pictogram intended to be displayed on the second display window of the main display means without being displayed on the first window of the main display means.

Abstract: A device (10) for assisted piloting of an aircraft having a rotary wing with a plurality of second blades (3?) and a propulsion unit with a plurality of first blades (2?). The device includes control means (30, 40) for delivering a movement order (O) for moving in a direction, said device (10) having a processor unit (20) for transforming said order (O) into an acceleration setpoint (C) along said direction, and then for transforming said acceleration setpoint (C) into at least one required longitudinal attitude setpoint (?*) that is transmitted to a first automatic system (26) for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades (3?), and into a first required load factor setpoint (Nx*) in a longitudinal direction that is transmitted to a second automatic system (25) for maintaining load factor by controlling the collective pitch of the first blades.

Abstract: A present novel and non-trivial system, device, and method for generating object symbology are disclosed. A system may be comprised one or more aircraft systems and a cockpit display system comprised of a system configuration file, a plurality of definition files, and a windows generator (“WG”). The WG may be configured to perform initialization and run-time operations. The initialization operation may be comprised of retrieving a system configuration file; retrieving a first definition file comprised of a first layer; and retrieving one or more second definition files comprised of one or more second layers. The run-time operation may be comprised of receiving a first-layer widget data set; receiving one or more second-layer widget data sets; determining the screen position of each object located within a view frustum; and generating a pixel data set in response to the determination.

Abstract: A present novel and non-trivial system, device, and method for generating object symbology are disclosed. A system may be comprised one or more aircraft systems and a cockpit display system comprised of a system configuration file, a plurality of definition files, and a windows generator (“WG”). The WG may be configured to perform initialization and run-time operations. The initialization operation may be comprised of retrieving a system configuration file; retrieving a first definition file comprised of a first layer; and retrieving one or more second definition files comprised of one or more second layers. The run-time operation may be comprised of receiving a first-layer widget data set; receiving one or more second-layer widget data sets; determining each screen array cell; and generating a pixel data set in response to the determination.

Abstract: A method and system for providing taxiway navigational information to a crewmember of an airplane taxiing at an airport. An airport taxiway navigation system (“ATNS”) that executes on an onboard computer system that displays a map of the taxiways of an airport, receives the name of each taxiway of the taxi route specified by the taxi clearance, and highlights the taxiways on a displayed map to provide a visual indication of the cleared taxi route for the crewmembers.

Abstract: In the examples described the forward-looking radar generated real-time terrain model (or in an alternative example in combination with a terrain database), can allow the use of a radio altimeter to compute aircraft vertical position relative to the runway threshold. Such a system typically provides improved accuracy for precision landings.

Abstract: Present novel and non-trivial methods for presenting traffic information are disclosed. In a first method, data representative of ownship position, first traffic, and second traffic are received by a traffic symbology generator (“TSG”). The traffic is divided into zones and a correlation between the targets of the traffic is determined. A traffic symbology data set is generated by the TSG based upon the results of the correlation(s). In a second method, data representative of ownship position and first traffic, runway references, and a selectable display range are received by the TSG. The traffic is divided into zones, and a traffic symbology data set is generated by the TSG thereafter. In a third method, data representative of ownship position and first traffic are received by the TSG. The traffic is divided into zones, and a traffic symbology data set is generated by the TSG thereafter.

Abstract: According to one embodiment, an aircraft part environmental stress analysis system includes a part failure repository, a part history repository, and a failure analysis engine. The part failure repository is configured to store a plurality of failure records, each failure record identifying a failed aircraft part. The part history repository is configured to store a plurality of part records, each part record storing, for a failed aircraft part, at least one measurement of an aspect of a natural environment of which the failed aircraft part was subject to. The failure analysis engine is operable to compare the plurality of failure records to the plurality of part records and identify at least one potential environmental cause of failure for a plurality of failed aircraft parts based on the comparison.

Abstract: This method for automatic analysis of failure or state messages generated by at least one complex system is characterized in that it comprises the steps for integrating said messages to a database of failure or state messages, and for determining with a computer, for each of said messages, an index of overall interest characterizing a degree of relevance of said message, on the basis of at least one parameter representative of a frequency of occurrence of similar messages in said database, and a correlation between said or each representative parameter and a predefined number of indexes of overall interest. A corresponding analysis system is also provided.

Abstract: An exemplary embodiment relates to an aircraft system for detecting wires. The system includes a processor configured to actively sense a presence of a first object and a second object. The processor determines a location of the first object and the second object. The processor determines a potential location of a wire between the first object and the second object. The processor actively senses the wire by providing electromagnetic energy to the potential location.

Abstract: A method and apparatus are present for monitoring a runway. Data is received about the runway from a number of sensors associated with an aircraft while the aircraft performs an operation on the runway. A number of conditions are identified for the runway using the data received from the number of sensors.

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 invention concerns an aircraft comprising a cockpit situated outside the nose of the aircraft. The cockpit is situated in a lower part of a fin, the latter advantageously extending to a front end of the aircraft. Preferably, the aircraft has a lancet-shaped nose.

Abstract: Methods and systems are provided for improving pilot situational awareness during brown-over-brown display situations. An image is rendered, on a display, that includes one of, or both, rendered terrain and rendered sky. A sky veil is at least selectively rendered on a portion of the display. The sky veil, when rendered, is rendered at least partially transparent and in a manner that portions of the sky veil that overlap with rendered sky are not discernable, and rendered terrain is viewable through portions of the sky veil that overlap with terrain.

Abstract: The present invention relates to a method and a system for assisting in the landing or the decking of a light aircraft, the method being implemented by a system comprising a device on the ground for locating the aircraft, the aircraft having an onboard signal sender, the method comprising at least the following steps: the locating device on the ground uses signals sent by the sender to determine the position and/or movement of the aircraft; said device transmits the previously determined aircraft position and/or movement data to the aircraft; display means show at least some of said data made accessible to the pilot of the aircraft. The invention applies in particular to the field of civil light aeronautics, notably for facilitating the landing of pleasure aeroplanes, small transport aeroplanes and helicopters.

Abstract: The invention concerns an aircraft including a cockpit comprising a viewing surface for piloting giving at least one pilot a view of an outside scene comprising the environment of the aircraft extending forward of the aircraft. At least part of said viewing surface for piloting is free of any glazed surface and is formed by display means for a digital image representing at least part of an outside scene comprising the environment of the aircraft extending forward of the aircraft.

Abstract: A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

Abstract: A method and apparatus are provided for operating a network data processing system on an aircraft. A number of operations are performed in a virtual machine on the aircraft. The virtual machine runs on a processor unit in the network data processing system on the aircraft to create a simulated computer environment. The virtual machine accesses resources of the processor unit for performing the number of operations using a host operating system on the processor unit. A current state of the aircraft is identified by the network data processing system. Running of the virtual machine is managed based on the current state of the aircraft and a policy for managing the virtual machine for different states of the aircraft.

Abstract: Methods and systems are provided for monitoring an aircraft. An exemplary method involves capturing, by a computing system at a ground location, a flight tracking image associated with the aircraft that is displayed on a first display device at the ground location, and communicating the captured flight tracking image to the aircraft for display on a second display device onboard the aircraft.

Abstract: A method and a device is provided for supplying, in summary fashion on a single page of a screen for each point, the data relating to a flight plan. The method makes it possible to establish relevant groups of information according to the situation of the flight and to summarize the display of the data in folded-up mode or in an unfolded lateral mode. The unfolded display offers, on one and the same page, a more precise detail of the situation, by ergonomically and intuitively showing in the columns the predictions in relation to a type of constraint.

Abstract: A computer-implemented system and method for the processing and presentation of aviation information is disclosed. At plurality of flight information is received over a digital network and is stored in at least a database. The database includes aviation information. Upon receiving a user request, a server retrieves a result set from the database and transmits it to the requesting user. Subsequently, updates as to a flight identified in the request are transmitted at a selected rate, which may be modified automatically based on one flight characteristic, for subsequent display. In one form, the results may be presented to the user in the form of digital map having aircraft images.

Abstract: The detection device includes, but is not limited to a device that is configured to determine a control error corresponding to the difference between a first control instruction and a control surface position, a second device that is configured to calculate the difference between this control error and a second control instruction in such a way as to form a comparison signal, and a third device that is configured to detect a jamming of the control surface if this comparison signal is greater than a threshold value.

Abstract: A method of operating an aircraft comprising a cockpit with a flight deck having at least one flight display, a pilot's seat facing the flight deck, and a synthetic vision system producing a synthetic image for displaying on the at least one flight display.

Abstract: An intuitive display including a visual representation of a maximum admissible angle of attack on a pitch scale giving the crew of an aircraft a visual recognition of an imminent stall, or of a stall, together with real assistance with piloting during the stall until the aircraft has come out of the stall completely.

Abstract: A system and method of transmitting data from an aircraft includes a PC card that acquires aircraft data and transmits the aircraft data over a radio frequency communications signal into the skin of the aircraft, which radiates the radio frequency communications signal to a location remote from the aircraft.

Abstract: A method and apparatus comprising a bus system and a plurality of control units connected to the bus system. The plurality of control units are each configured to control a same number of hardware systems in a vehicle, store a number of parameters used to control the number of hardware systems, and synchronize the number of parameter stored using the bus system in response to a change in the number of parameters at a selected control unit in the plurality of control units.

Abstract: An aircraft based radar system is provided. The radar system includes processing electronics configured to estimate a vertical loading on the aircraft using radar return data and a time value.

Abstract: Traffic awareness systems and methods include receiving data regarding a first aircraft and determining the location of the first aircraft relative to the location of a second aircraft. An indication of the first aircraft may be provided to a display based on a determination that the relative location of the first aircraft is within a field of view associated with the display.