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: 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.

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: The device displays on one and the same indicator (11) of display means (7) indication elements (14, 16, 17, 33) illustrating as a percentage the engine start progression or the current sub-idle state of the turbine engine, a margin to a possible exceeding of a limit temperature of the turbine engine, a margin to a possible exceeding of a maximum temperature of the turbine engine and a margin to a possible failure of the start that is generated by a too low speed increase of the turbine engine.

Abstract: A system and method for displaying additional traffic information beyond that received from an ADS-B or other transponder communication. Such additional traffic information may be displayed on a display screen within a cockpit, and may include such things as an aircraft's make, model, manufacturer, or other information. The additional information may be displayed as text, or one or more pictures, icons, or symbols that correspond to this additional information, or any combination of text and such items. The additional information may be determined from one or more databases that correlate information received in the transponder communication to the additional information that is not contained within the transponder communication.

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

Abstract: A method, apparatus, and computer program product for displaying information about runways. A runway for an aircraft is identified when the aircraft is within a selected distance of the runway. A number of graphical indicators are displayed on a display in a flight deck. The number of graphical indicators corresponds to a number of features of the runway present in a field of view for an eye reference point in the flight deck.

Abstract: An arrangement for cross monitoring two independent signals. The arrangement a calculator configured to calculate a value depending upon a signal value, a drift value and a feedback value, and a determining unit configured to determine a larger of the calculated value and a first predetermined value. The arrangement also includes a comparing unit configured to compared the determine larger value with a second predetermined value and a delaying unit configured to delay the determined larger value and change status of the larger value to become an updated feedback value to be provided to the calculator. The arrangement is characterized in that the signal value includes information about an absolute value of a difference between the two independent generated signals.

Abstract: This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.

Abstract: A method that includes identifying a desired signal connectivity through a switch matrix, where the switch matrix includes a plurality of switching elements, and where the switching elements are selectively operable in a plurality of states to provide a plurality of signal paths for routing signals through the switch matrix. The method also includes identifying a sorting network model that corresponds to a topology of the switch matrix, applying a sorting algorithm to the sorting network model, and determining, based on the results of applying the sorting algorithm, operational states of the plurality of switching elements to provide signal paths corresponding to the desired signal connectivity.

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

Abstract: A display system and method for providing a display. A display system includes a computer processor, the computer processor being configured to receive information from a plurality of sensors. The computer processor is further configured to detect an abnormal situation, based on information received from the plurality of sensors. The display system further includes a database including abnormal situation response procedures in operable communication with the processor, wherein the database is configured to provide the processor with the abnormal situation response procedures upon the detection of an abnormal situation. The display system further includes a display device in operable communication with the processor, wherein the display device is configured to display information from the sensors regarding the abnormal situation and the abnormal situation response procedures.

Abstract: Methods, systems, and computer-readable media are described herein for displaying MPA procedures on a display unit of an aircraft. An assigned MPA approach path to an arrival runway is received at the aircraft. Data regarding a number of predefined MPA approach paths associated with the arrival runway are retrieved, and the assigned MPA approach path is displayed on the display unit in conjunction with other of the predefined approach paths associated with the arrival runway.

Abstract: Methods, systems, and apparatus for tab-pane-based flight plan management interface are disclosed. The tab-pane-based flight management interface system (FMIS) is optimally Layered and Multi-Indexed (LMI) such that the management of flight management (FM) functions and associated parameters that affect the airplane's flight are easily and efficiently operable by pilots. The LMI-FMIS provides a flexible tab-pane-based architecture that allows pilots to start a flight plan modification, proceed to engage in other tasks not related to the modification, and return to the pending modification to continue the modification process. The LMI-FMIS also provides task-oriented menu structures that provide pilots tailored options or menus applicable to the task at hand thus efficiently guiding pilots to complete a task while maintaining easy access to information that was displayed prior to the commencement of the task.

Abstract: Methods and apparatus are provided for context sensitive notifications of incoming digital communications on an aircraft. The method comprises receiving a new datalink message from a sender on a device, the datalink message including a unique identifier associated with the sender, and determining if the sender is a new sender based on the unique identifier. The method comprises determining if the device is involved in an active exchange of datalink messages based on activity data associated with the device and outputting a first alert that the new datalink message has been received at an alert level below a current alert level if the sender is not a new sender and the device is engaged in the active exchange of datalink messages.

Abstract: A method and module for displaying a munition release envelope.

Abstract: In a centralized navigation information management system installed on board an aircraft which is in a current position at a current time, the aircraft having a warning management system and a route management system with means for creating a route plan, the route plan having a future route plan corresponding with the part of the route plan beginning at the current position and at the current time, the system includes: means for creating a task comprising at least one task parameter relating to an item of navigation information, including a task variable corresponding to a condition of execution of the said task, the means for creating a task having means for determining a predicted time meeting the execution condition; and means for detecting a possible inconsistency between the created task and the route plan or the future route plan and for transmitting, when an inconsistency is detected, a message relating to the inconsistency to a first display means of a centralized warning management system to display

Abstract: The display system (1) comprises means (5, 11A, 14) to take into account a recorded symbology, in the event of a malfunction in the emission of a symbology, to perform a display of symbology.

Abstract: Methods and apparatus are provided for shared situational awareness between a first display and a second display onboard an aircraft. The first display and the second display are associated with a respective first user input device and second user input device that each receive user input with respect to the first display and the second display. The method includes receiving a request to activate a shared situational awareness system to enable telestration between the first display and the second display. The method also includes determining, based on user input received from the first user input device and the second user input device, if a request to change a background image displayed on the first display and the second display has been received, and outputting a different background image for display on the first display and the second display, which is generated from data relating to the operation of the aircraft.

Abstract: A flight management system is provided for generating a variable thrust cutback during aircraft departure. The flight management system includes memory storing a sound exposure level limit for a navigation flight and storing expected sound exposure levels for an aircraft, and one or more inputs for receiving sensed aircraft variables including altitude and airspeed. The system also includes a processor for processing the sensed altitude and airspeed and stored sound exposure levels. The processor further computes an engine thrust value that complies with the sound exposure level limit based on the altitude, airspeed and the sound exposure levels for controlling aircraft throttle during departure.

Abstract: Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.

Abstract: A system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, cruise, descent, landing) to pilots in response to situations wherein the measured air data should not be relied upon. This information is presented in an intuitive and expedient manner exactly when and where it is needed on the primary flight display. The displayed information dynamically changes in response to airplane parameters.

Abstract: Aircraft system and method are provided for a first aircraft in an airport environment, the airport environment including a second aircraft. The system includes a sensor on the first aircraft configured to determine a temperature profile of engine exhaust from the second aircraft; and a processing unit coupled to the sensor and configured to construct a velocity profile of the engine exhaust from the second aircraft based on the temperature profile and to generate a warning for a pilot of the first aircraft based on the velocity profile.

Abstract: A system and method for illuminating one or more sidestick controllers within a cockpit of an aircraft is described. In some embodiments, the system includes a sidestick controller having lighting components that display lighting behaviors representing the movement and/or control of an aircraft. In some embodiments, the system illuminates various different lighting components on a sidestick controller based on information received from aircraft control systems, cockpit lighting systems, and other systems associated with an aircraft.

Abstract: The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display.

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

Abstract: A method for selecting and displaying a flight path for an aircraft on a display of a flight deck of the aircraft that allows a user to input a selected flight path on a map displayed on the display. A final flight path will be displayed on the display of the flight deck that is based on the input of the selected flight path.

Abstract: A feathering, flapping and rotor loads indicator for use in a rotorcraft includes a calculation unit configured to calculate (a) a current temperature of a bearing of the rotor assembly using a first calculation model, (b) a projected temperature of the bearing using the first calculation model and (c) a load exerted on a selected component of the rotor assembly using a second calculation model, the first and second calculation models adapted to calculate, respectively, the projected and the current temperatures of the bearing and the load exerted on the selected component based on flight control parameters; and a display unit configured to display on a common scale a movable indicator, the movable indicator being driven by the highest value between the projected temperature of the bearing and the load exerted on the selected component. The display unit displays another movable indicator driven by the current temperature of the bearing.

Abstract: An avionics control and display unit (CDU) in an integrated avionics system includes a display unit having a touch screen configured to detect touch input. The CDU is configured to have a first mode of operation or a second mode of operation. When the first mode of operation is selected, the display unit is configured to display control indicia to facilitate the control of one or more functions associated with the avionics system. When the second mode of operation is selected, the display unit is configured to enable a cursor control area to facilitate manipulation of indicia displayed by a display device such as a primary flight display (PFD) or a multifunction display (MFD), and so forth, via touch input to the touch screen over the cursor control area.

Abstract: Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring aircraft.

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: An installation for detecting and displaying the failures of the functional systems of an aircraft is described. The installation can include both a general alarm system (4) connected to said functional systems (2) and to the auxiliary alarm detection means (5) originated from said functional systems, and a complementary alarm system (6), connected to said functional systems (2), independently from the general system (4), and able to indicate a breakdown not detected by the general system on the instrument panel of the cockpit.

Abstract: A present novel and non-trivial system, device, and method are disclosed for generating an ILS-based highway-in-the-sky (“HITS”). The system is comprised of an image data generator configured to receive navigation data, ILS deviation data, and navigation reference data from applicable data sources, where the navigation data is representative of ownship position, the ILS deviation data is representative of localizer and glide slope deviation, and navigation reference data is representative of data corresponding to an ILS approach of a runway; determine two instantaneous waypoints as a function of the received data; generate image data representative of a HITS, where the proximal and distal ends of the HITS are based upon the two instantaneous waypoints; and provide the image data to a display unit, whereby the HITS is presented on the screen of a display unit.

Abstract: A method and hold path computation system for automatically generating a hold path for an aircraft flying in a holding pattern, wherein the holding pattern is defined by one or more orbits within a selectable holding area are provided. The system includes a processor configured to receive a hold departure time indicating a time the aircraft is to leave the hold path to meet a required time of arrival (RTA) at a waypoint, determine a present position of the aircraft within the holding pattern, and determine an amount of time to complete a current hold orbit. The processor is also configured such that if the determined amount of time to complete a current hold orbit is less than or equal to the hold departure time, maintain the aircraft flying in the holding pattern and determine an amount of time by which to shorten the next orbit to exit the holding pattern at the hold departure time.

Abstract: The invention relates to an aircraft navigational aid system with 3D display including an anti-collision device, with means of storing data representing obstructions, means for calculating a representation of the obstructions in a three-dimensional space and a device for displaying the obstructions data in three dimensions. The system includes means for augmenting the display of the representation of the area of hazardous obstructions with at least two indicator objects for the said area of hazardous obstructions disposed together in such a manner as to form a third object targeting the localization of the point in the area of hazardous obstructions closest to the aircraft. The invention also relates to the method of display of the indicator objects in a three-dimensional display.

Abstract: A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft.

Abstract: According to one embodiment, a center pedestal display includes a plurality of mounting faces and a high-resolution screen. The plurality of mounting faces include a first mounting face that is substantially parallel with a first surface of a pedestal mounting block of an existing instrument pedestal and a second mounting face that is substantially parallel with a second surface of the pedestal mounting block, the second surface intersecting the first surface at an angle such that the first surface is not parallel to the second surface. The existing instrument pedestal includes one or more pedestal gauges and one or more pedestal switches. The high-resolution screen is configured to display information comprising at least some information provided by the one or more pedestal gauges. The high-resolution screen is approximately 6×8 inches and has a resolution of at least 1024×768 pixels.

Abstract: A method and a device for displaying meteorological data on an aircraft screen including generating and displaying on the screen an automatic dynamic transition between a start view and an arrival view, preferably in perspective. The dynamic transition corresponds to a successive display of views between the start view and the arrival view, each view including a symbol indicating the current position of the aircraft and meteorological data.

Abstract: This aircraft control cabin comprises an avionics display device with multiple fixed screens (10a-10d) and at least one screen (15, 16) as an accessory, designed to be a replacement screen or extra screen for the avionics display system. The screen (15, 16) is a touch screen housed in a retractable tablet which slides underneath an instrument panel in the control cabin, the touch screen (15, 16) being designed to occupy a stowed position underneath the instrument panel, a first position of use in the retractable tablet in which the touch screen (15, 16) acts as a means of interaction for controlling various items in the control cabin and a second position of use in which the touch screen (15, 16) is put in a position in which it replaces or supplements a screen (10a-10d) belonging to the avionics display system. Use in an aircraft.

Abstract: A display system for an aircraft includes a controller in communication with a display. The controller receives a category associated with a phase of flight of the aircraft. Information related to operation of the aircraft and associated with the received category is displayed on the display.

Abstract: An instrument panel including a plurality of user interface components respectively configured to receive or generate an electrical signal and one or more electronic apparatus, such as a bus expander, configured to exchange data between the plurality of electronic user interface components and a bus. With embodiments, the instrument panel is configured without a microprocessor or a micro-coded component coupled to the bus.

Abstract: A device for aiding flight for an aircraft includes means for locating the localities situated in the operational area for rescue missions. The device is able to present to the crew a landmark of the positions of the localities in relation to the position of the aircraft, this landmark also indicating information connected with navigation and to flight regulations for each of the localities. The device relates to operations aircraft and more particularly rescue helicopters.

Abstract: A display system and method for providing a display. A display system includes a computer processor, the computer processor being configured to receive information from a plurality of sensors. The computer processor is further configured to detect an abnormal situation, based on information received from the plurality of sensors. The display system further includes a database including abnormal situation response procedures in operable communication with the processor, wherein the database is configured to provide the processor with the abnormal situation response procedures upon the detection of an abnormal situation. The display system further includes a display device in operable communication with the processor, wherein the display device is configured to display information from the sensors regarding the abnormal situation and the abnormal situation response procedures.

Abstract: An integrated system for providing minimum equipment decision support for an aircraft including means for procuring onboard aircraft data and providing a cockpit message. Minimum equipment list (MEL) constraints and offboard flight plan related information are procured. The onboard aircraft flight data, minimum equipment list constraints, and offboard flight plan related information are synthesized to enable holistic flight dispatch determinations within the current fault condition of the aircraft.

Abstract: The invention relates to a system and a method for calculating flight predictions of an aircraft in which an intermediate prediction horizon is defined between the flight phase and the leg. This horizon, that is called vertical section, is defined such that the limit conditions that are applicable to it, for example the target speed, target altitude, characteristic altitude and maximum end-of-section distance, are valid for the entire vertical section. Thus, it is not necessary, in calculations to check the compatibility of the flight parameters with the applicable constraints, to arbitrarily select the constraint that must be given priority. Furthermore, this intermediate level architecture allows for a greater modularity of the prediction management software and therefore a greater factorization of the developments and greater ease of maintenance.

Abstract: The invention is embodied in the form of a flight simulator in the conditions of vortex danger and in conditions when a pilot is informed about the possibility to penetrate into said dangerous area of vortex sheddings produced by a vortex generator.

Abstract: Technologies are described herein for displaying runway status information to a pilot in an aircraft. In one aspect of the present disclosure, a runway status display module displays a runway status indicator indicating the runway status information at a fixed scale independent of a scale of the map on a map display. In another aspect, the runway status indicator is displayed on a non-map display indicating the runway status of the runway. In another aspect, the runway status indicator is displayed at a position independent from a depiction of the runway on the aircraft display.

Abstract: The present general inventive concept relates to a system of method having an electronic flight display that meets the FAR 23.1311(b) regulatory requirement for redundant backup instruments in the cockpit. The present general inventive concept also provides a system and method to detect failures, obstructions, or improper operation of the aircraft pitot pressure sensing system using a combination of dissimilar sensor data that is independent from each other, e.g., allocated from different sources and employed for different purposes on different displays, and displays information on an avionics display screen.

Abstract: An apparatus for pressurizing an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure comprises an air supply line which at a first end is connectable to a pressurized air source and which at a second end is connectable to the aircraft cabin structure so as to supply pressurized air from the pressurized air source into the aircraft cabin structure, an air supply valve disposed in the air supply fine, a pressure sensor for sensing the pressure inside the aircraft cabin structure and for providing signals indicative of the pressure inside the aircraft cabin structure, an air discharge line which at a first end is connectable to the aircraft cabin structure and which at a second end is connectable to an air discharge opening so as to discharge air from the inside of the cabin structure to the air discharge opening and an air discharge valve disposed in the air discharge line.

Abstract: A system and method for providing an aircraft noise advisory during departure and/or arrival of an aircraft are disclosed. In one embodiment, predefined allowable aircraft noise level information associated with a plurality of aircraft noise sensors located in the vicinity of airports are obtained. Further, predefined allowable aircraft noise level information associated with one or more of the plurality of aircraft noise sensors is presented on a display device in the aircraft, based on a current location of the aircraft, upon receiving noise data request from a pilot. Furthermore, current aircraft noise level information is obtained from one of the one or more aircraft noise sensors. In addition, the current aircraft noise level information is compared with predefined allowable aircraft noise level information associated with the one of the one or more aircraft noise sensors. Also, the aircraft noise advisory is displayed based on an outcome of the comparison.