Abstract: The invention concerns a display system for an aircraft. The display system (1) comprises means for automatic reconfiguration (4), upon detecting failure of a screen (E1 to En) of said system for displaying the image which is associated with the failed screen on an associated valid screen having lesser priority based on priority rules.

Abstract: An aircraft display system is provided that is configured to render a perspective display having a field of view. The aircraft display system includes a monitor and a processor coupled to the monitor. The processor is configured to generate a map display on the monitor. The map display indicates the value of at least one parameter of the field of view of the perspective display.

Abstract: A flight information communication system has a plurality of RF direct sequence spread spectrum ground data links that link respective aircraft-resident subsystems, in each of which a copy of its flight performance data is stored, with airport-located subsystems. The airport-located subsystems are coupled by way communication paths, such as land line telephone links, to a remote flight operations control center. At the flight operations control center, flight performance data downlinked from plural aircraft parked at different airports is analyzed. In addition, the flight control center may be employed to direct the uploading of in-flight data files, such as audio, video and navigation files from the airport-located Subsystems to the aircraft.

Abstract: A flight information communication system has a plurality of RF direct sequence spread spectrum ground data links that link respective aircraft-resident subsystems, in each of which a copy of its flight performance data is stored, with airport-located subsystems. The airport-located subsystems are coupled by way communication paths, such as land line telephone links, to a remote flight operations control center. At the flight operations control center, flight performance data downlinked from plural aircraft parked at different airports is analyzed. In addition, the flight control center may be employed to direct the uploading of in-flight data files, such as audio, video and navigation files from the airport-located subsystems to the aircraft.

Abstract: Methods and systems are provided for displaying an unusual attitude of an aircraft in a head-up display system. The system comprises a projection unit configured to project the unusual attitude of the aircraft and a processor coupled to the LCD projection unit. The processor is configured to control the LCD projection unit during the unusual attitude of the aircraft to produce an attitude indicator of the aircraft and a horizon symbol. The horizon symbol divides the attitude indicator into a first region having a first display characteristic and a second region having a second display characteristic different from the first display characteristic. The first display characteristic is substantially uniform throughout the first region, and the first region indicates a ground with respect to the aircraft.

Abstract: The field of the invention is that of the display in map form of an operating zone of an aircraft on a screen, and more particularly a method of processing topographic data of this operating zone of an aircraft in real time, based on a calculation of radials (R) centred on a reference point (O) defining an angular segment of topographic data. According to the invention, the method includes a subdivision of the operating zone to be mapped into a plurality of angular segment sections, each forming an individual zone (3), and an assignment of a processing priority and a refresh frequency specific to each individual zone defined according to a criterion of operational interest of the element to the aircraft.

Abstract: The invention concerns a piloting indicator (1) comprising data sources (2) which determine the parameter values concerning the propeller and the turbine of the turboprop, as well as the parameter values concerning the aircraft, processing means (3) which calculate based on said values, a power parameter which takes into account the ratio between the current power of the turboprop engine and the maximum power obtained without air bleed at sea level in standard atmosphere, and display means (5) which display, on a viewing screen (7), at least one characteristic symbol (11) illustrating said power parameter.

Abstract: A system and method for displaying aircraft glide slope includes determining a glide slope deviation that is representative of a difference between a desired aircraft glide slope and an actual aircraft glide slope. A glide slope icon that is representative of the desired aircraft glide slope and a glide slope deviation icon that is representative of the determined glide slope deviation are simultaneously rendered on a display.

Abstract: A spatial data search method, system and apparatus for identifying particular data of significance around a reference vector through the spatial data. The method involves determining a reference vector within a spatial region for which spatial data exists, loading a portion of the spatial data including the data around the reference vector into a memory buffer, and searching the spatial data in a prioritized order. The method, system and apparatus have particular utility in searching geographic data for a terrain awareness and warning system (“TAWS”) and display in an aircraft. Embodiments of the present invention provide advantages over existing sequential and radial search methods, significantly reducing the processing and calculations required and providing faster alerts to pilots.

Abstract: A smart airport automation system gathers and reinterprets a wide variety of aircraft and airport related data and information around unattended or non-towered airports. Data is gathered from many different types of sources, and in otherwise incompatible data formats. The smart airport automation system then decodes, assembles, fuses, and broadcasts structured information, in real-time, to aircraft pilots. The fused information is also useful to remotely located air traffic controllers who monitor non-towered airport operations. The system includes a data fusion and distribution computer that imports aircraft position and velocity, weather, and airport specific data. The data inputs are used to compute safe takeoff and landing sequences, and other airport advisory information for participating aircraft.

Abstract: The present invention is a method and system of aircraft surface operations guidance on a head up display. An aircraft surface operations guidance method includes the following steps. At time t1, a taxi guidance cue and a trend vector are displayed on a head up display of an aircraft. The taxi guidance cue represents a desired position of an aircraft control point of the aircraft at time t2. The trend vector represents a predicted path of the aircraft control point from time t1 to time t2 based on a state of the aircraft at time t1. The trend vector includes a tip representing a predicted position of the aircraft control point at time t2. The tip is maintained within the taxi guidance cue so that the aircraft control point may reach the desired position at time t2.

Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.

Abstract: A holding pattern aid apparatus to enable a pilot in instrument conditions to instantly visualize a holding pattern and determine an appropriate entry procedure, is disclosed. The aid is configured to attach to a kneeboard while permitting the pilot to flip the display from right to left holding pattern with one hand or even the flick of a finger. The apparatus also indicates the appropriate teardrop outbound course and parallel intercept course, as well as providing instant reciprocal headings and a DME Arc aid. A lanyard attach point enables the pilot to quickly find the holding pattern aid when loose and prevents the aid from becoming lost in the cockpit should it become detached from the kneeboard.

Abstract: An aircraft emergency lighting system including: a plurality of units having communication devices arranged to communicate wirelessly with a master controller, wherein each unit is wired to a common power supply for powering the unit in a first mode of operation and has its own back-up battery power supply for powering the unit in a second mode of operation, and wherein the device is provided for off-load testing the back-up battery power supply of each unit and indicating if the unit is operational.

Abstract: The invention relates to a method and system for supporting pilots in landing helicopters in visual flight under brownout or whiteout conditions. According to the invention, 3D data of the planned landing site are generated during the approach for landing, and are accumulated into a 3D representation of the landing site with the aid of position and attitude data of the helicopter. From this 3D representation, a virtual external view is continuously generated corresponding to the perspective of the actual position and attitude of the helicopter and is displayed for the pilot. A control routine ensures that no 3D data of the planned landing site that are generated under brownout or whiteout conditions are taken into account in the accumulation of the 3D representation.

Abstract: Systems and methods for handling incoming aircraft operation instructions are disclosed. A method in accordance with one embodiment of the invention includes receiving from a source off-board an aircraft an instruction for changing a characteristic of the aircraft, and automatically displaying at least a portion of the instruction at a first display location. In response to receiving a first input signal directed by an operator onboard the aircraft, the method can further include displaying at least a target portion of the instruction at a second display location, without the instruction being manually regenerated, and without the instruction becoming part of a flight plan list. In response to receiving a second input signal directed by an operator, the method can further include displaying at least a target portion of the instruction at a third display location, again without the instruction being manually regenerated.

Abstract: A flat panel display system for an aircraft display includes a graphics rendering computer for rendering of anti-aliased graphical imaging data derived from aircraft sensors for full-field imaging on a cockpit display screen. A comparator processor independently generates, from the same sensor data, a selected subset or “points of light” of the display screen image and compares the points of light data to the data generated by the rendering computer for the same display screen pixel locations. The minimized processing requirements and simplified design of the comparator processor enable ready FAA certification of the comparator processor, whereas the extreme complexity and processing operations required of the rendering computer make FAA certification thereof unusually time consuming and expensive.

Abstract: An integrated communication system in an aircraft is provided. The system includes a plurality of solid state flight deck modules in an integrated flight deck panel, wherein the solid state flight deck modules include a microcontroller for interfacing with at least one data bus controller via a local bus; and a light emitting diode (LED) module for controlling backlit illumination of the integrated flight deck panel. The controller sends information to plural solid state flight deck modules via local buses and uses a system bus to communicate with aircraft subsystems. The controller also uses a central power supply module to supply regulated power to the plural solid state flight deck modules. Furthermore, at least one solid state flight deck module includes an integrated panel brightness control module, master brightness control module and/or a master dim and test control module.

Abstract: Methods and systems for displaying aircraft operations information are disclosed. A method in accordance with one embodiment includes receiving operations information, presenting a first portion of the information over a first area of a display medium having a first size, receiving a signal corresponding to an instruction to increase a fraction of the display medium occupied by the operations information, and presenting at least the first portion of the operations information over a second, larger area of the display medium. Multiple display media can be controlled by independent selectors, with each selector having two portions, one to select categories of aircraft operations information, and another to present groups of selectable options corresponding to each of the individual categories of operations information.

Abstract: One embodiment of the present invention includes an aircraft instrumentation system for a cockpit instrument panel having a first device associated with a first pilot of an aircraft and positioned on the instrument panel substantially in front of the first pilot. The first device may include a first display and a first controller, which may have a set of controls for controlling the first display and aircraft systems. The instrumentation system may also include a second device associated with a second pilot of the aircraft and positioned on the instrument panel substantially in front of the second pilot. The second device may include a second display and a second controller, which may have a set of controls for controlling the second display and the aircraft systems. The instrumentation may be configured such that at least one of the first display and the second display presents attitude, altitude and airspeed at all times.

Abstract: A flight instrument displays azimuth information in combination with horizon information and other optional information such as altitude and/or airspeed. Azimuth information is displayed using an elliptical pattern placed below a horizon line displaying horizon information. The horizon information may be based on gyro enhanced vertical speed and/or vertical axis information. The elliptical pattern may be representative of a horizontal circular heading indicator viewed from above and behind the circular indicator. In one embodiment, the elliptical azimuth pattern moves in response to movement of the horizon line to maintain position below the horizon line. Airspeed and/or altitude information may be displayed at the sides of the screen area using a circular arc display pattern.

Abstract: The present invention relates to an avoidance system and method for directing an aircraft away from an exclusion zone. The exclusion zone may be any three dimensional space for example about a building or city. The avoidance system uses a constant signal from a ground based transmitter and an aircraft's receiver which receives and processes the signal and activates the avoidance system by engaging the flight director system or autopilot to steer away from the exclusion zone.

Abstract: Method and system for monitoring and comparing, in real time, performance of an aircraft during an approach to touchdown along a conventional approach path and along a contemplated modified approach path to touchdown. In a first procedure, a flight parameter value at a selected location is compared and displayed, for the planned path and for the modified path. In a second procedure, flight parameter values FP(tn) at a sequence {tn}n of measurement times is compared and displayed, for the planned path and for a contemplated or presently-executed modified path. If the flight parameter for the planned path and for the modified path differ too much from each other, the pilot in command has an option of terminating the approach along the modified path.

Abstract: Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information. A method in accordance with one aspect of the invention includes displaying at least one first indicator to an operator of the aircraft, with a first indicator corresponding to a first instruction input by the operator for directing a first aircraft behavior and implemented upon receiving an activation instruction from the operator. At least one second indicator corresponding to a second instruction for directing a second aircraft behavior at least proximately the same as the first aircraft behavior is displayed, with the at least one second instruction to be automatically implemented at a future time. The at least one second indicator is at least approximately the same as the at least one first indicator. Indicators can be hierarchically organized to simplify presentation and reduce pilot training time.

Abstract: The documentary assistance device (1) comprises sources of computer data (S1 to Sn, B1 to Bp) relating to said aircraft, to elements of the latter, as well as to the outside environment, an interrogation means (2) capable of being activated by an operator so as to generate a request for information relating to the execution of at least one particular task, an information presentation means (5), and a central processing unit (6) searching the data sources (S1 to Sn, B1 to Bp) in response to the creation of a request for information by the interrogation means (2), for data relating to the execution of the task, collecting these data and transmitting them, in the form of information, to the information presentation means (5) with a view to their presentation to the operator.

Abstract: A method, system, and apparatus, for providing audio feedback regarding the operation of an aircraft. In one aspect, microphones are placed next to sound sources, which could be components of the aircraft. Audio inputs are received from the microphone and analyzed based on a psycho-acoustic model to provide settings, such as level, pan, and equalization, to an automatic mixer. The automatic mixer mixes the sounds based on the settings and provides audio output to the pilot of the aircraft. The pilot can then use the audio output to more effectively monitor the operations of the aircraft components, which might otherwise be difficult or impossible to hear.

Abstract: The invention relates to an aircraft navigation aid method. It comprises the following steps of defining an area to be sensed to the right and to the left of a first hypothetical path of the aircraft, sensing, for each of the two areas to be sensed to the right and to the left, a corresponding predefined underlying relief, in order to identify dangerous sub-zones to the right and/or to the left, computing, for each of the dangerous sub-zones to the right and/or to the left, a time ?T remaining to begin an avoidance maneuver before a point of no return, and determining for the dangerous sub-zones to the right a minimum ?T denoted ?T right and/or for the dangerous sub-zones to the left a minimum ?T denoted ?T left, establishing a navigation aid from ?T right and/or ?T left.

Abstract: Method and system for analyzing and displaying one or more present flight parameter values FP(t) of an aircraft in motion at a measurement time tn, and for comparing the present flight parameter value with a selected percentage band, containing historical flight parameter data for similar conditions.

Abstract: A method of displaying traffic information is disclosed. The method comprises providing traffic information from at least one of a first and a second traffic information system to a traffic display system. The method also comprises choosing to display, by the traffic display system, traffic information from the first traffic information system when no traffic information from the second traffic information system is available. Further, the method comprises choosing to display, by the traffic display system, traffic information from the second traffic information system when no traffic information from the first traffic information system is available. The method further comprises choosing to display, by the traffic display system, traffic information from either the first traffic information system or the second traffic information system using a predetermined selection algorithm when traffic information is available from both traffic information systems.

Abstract: A method and system for displaying aircraft engine information. In one embodiment, the method includes directing the display of an icon that represents a qualitative, overall operational state of an aircraft engine, with the overall operational state being determined from a plurality of engine operating parameters. The method can further include directing a change in the display of the icon when the overall operational state of the aircraft engine changes from a first overall operational state to a second operational state. In a further aspect of this embodiment, the change in the characteristic of the icon can include a change in the color or other visual characteristic of the icon, and the color or other visual characteristic of the icon can correspond directly to instructions to the pilot for actions suggested or required as a result of the current engine operational state.

Abstract: Method and system for automatically displaying, visually and/or audibly and/or by an audible alarm signal, relevant weather data for an identified aircraft pilot, when each of a selected subset of measured or estimated aviation situation parameters, corresponding to a given aviation situation, has a value lying in a selected range. Each range for a particular pilot may be a default range, may be entered by the pilot and/or may be automatically determined from experience and may be subsequently edited by the pilot to change a range and to add or delete parameters describing a situation for which a display should be provided. The pilot can also verbally activate an audible display or visual display of selected information by verbal entry of a first command or a second command, respectively, that specifies the information required.

Abstract: A method and system for alerting an aircrew of terrorist activity in a cabin of an aircraft. When a terrorist or emergency situation is detected by a flight attendant, the flight attendant speaks an activation word, which turns the personal alert unit to an active mode. The flight attendant then says one or more specific words stored as a vocabulary within the personal alert unit. Upon recognition of a spoken word stored in the personal alert unit, the personal alert unit converts the recognized word or words into a signal sent to the cockpit via the ASU to the CDU. The CDU provides an indicator to the cockpit crew of the recognized words spoken by the flight attendant.

Abstract: A method for enhancing ground situational awareness to an aircraft operating at an airport is described. The method includes displaying, within the aircraft, runways and taxiways for the airport and displaying a position of the aircraft with respect to the runways and taxiway. A resolution of at least one of a runway, a taxiway, and an aircraft position is based on at least one of a selected resolution, a position and heading of the aircraft, a taxi speed, and a ground speed of the aircraft.

Abstract: Described is a heads-up display system for an aircraft having a rotating propeller within view of at least one occupant of the aircraft. The heads-up display system comprises a plurality of light-emitting elements disposed on a side of a propeller blade substantially facing at least one occupant of the aircraft. A graphics generator turns one or more of the light-emitting elements on the side of the propeller blade on and off in accordance with the rotation of the propeller to produce a graphical image that appears to at least one occupant of the aircraft to be superimposed on a background. The graphical image can be produced to conform to an object in the background upon which the graphical image is superimposed.

Abstract: A control device for the actuation of lamps in particular for internal aircraft lighting, wherein the control device (1) has an input (18) for the supply of an input signal and a plurality of outputs (21–28) for passing output signals to connected lamps (L1–L8). In the control device (1) a signal processing module (8–12) is preferably formed by a microprocessor and a preferably freely programmable electronic memory (13–17). The signal processing module (8–12) produces the output signals from the input signal in accordance with a conversion instruction deposited in the memory (13–17), wherein different conversion instructions can be stored in the memory (13–17) for output signals belonging to different outputs (21–28).

Abstract: An Aviation Weather Awareness and Reporting Enhancements (AWARE) system provides situational awareness by effectively filtering, analyzing and visualizing aviation weather data and specific hazard alerts in preflight, in-cockpit and controller applications. The AWARE system includes a temporal-spatial databases that filters weather data and a Bayesian network that assesses specific hazards in the filtered weather data in the context of pilot preferences, aircraft properties and airport properties. The filtered weather data and hazard alerts are then displayed on a client.

Abstract: A weather monitoring and prediction system that uses a fleet of aircraft to obtain data. Each aircraft has a local air data system that facilitates the measurement, recordation, and transmittal of local atmospheric data such as barometric pressure, and the corresponding temporal, positional, and altitudinal data. The data is electronically transmitted from each aircraft to a ground based processing system where it is stored. The data may then be transmitted to subscribing users such as aircraft, other weather data systems or to air traffic control centers in either a compiled form or in a raw form. Another embodiment also provides for measuring barometric pressure as a function of altitude at an in-flight aircraft.

Abstract: A method and apparatus is disclosed for displaying a dynamic parameter of an aircraft, the apparatus comprises a display unit receiving a display signal and displaying a scale that changes dynamically and non-linearly in accordance with a selected display algorithm, the display unit further displaying a pointer pointing to said scale in accordance with a reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter.

Abstract: A monitoring instrument that represents the state of n parameters is disclosed, where n is an integer greater than two. The monitoring instrument includes n axes having a common origination point. Each axis is configured to indicate one of the n parameters. The instrument also includes a polygon having n vertices, wherein each vertex is disposed along one of the n axes at a location indicating the state of the parameter indicated by said axis.

Abstract: A navigation device for navigating a vehicle to a point comprises a GPS receiver for receiving GPS signals, a processor connected with the receiver for processing the GPS signals, navigation data created by the processor, and a display page. The navigation data includes ground speed, altitude, vertical speed and rate of turn information, and the display page presents this information in individual graphic, circular displays representative of an aircraft instrument panel.

Abstract: A graphical display or presentation of lateral ANP/RNP information for RNAV environments. The display may also be adapted to present aircraft data for monitoring the vertical flight performance of an aircraft under RVSM.

Abstract: An improved method for correlating between targets in an air traffic control system. A methods or systems according to the invention compare selected components of a first target report to the components of a second target report, produce a confidence level on each component comparison, and determine whether to declare the targets similar based on the confidence level on each component compared. The first and second target reports may include ADS-B target reports and TIS target reports. The individual components of the reports may be range, bearing, track angle, and relative altitude. The methods or systems may use a fuzzy logic probability model to produce a continuous confidence level on each component comparison.

Abstract: A method for creating minimal data representing a source image is presented. The source image is divided into a grid of cells. A color is selected for each cell corner based on sampling an area defined by the cell corner. An indication of the selected color is stored in an array dependent on the co-ordinates of the cell corner in the source image.

Abstract: There is provided a method for displaying aircraft positions, which is capable of effectively avoiding the occurrence of near miss or collision. The method displays the terrain of an air space under air traffic control apparently in three dimensions on a display screen, displays aircraft marks at positions on the display screen so as to correspond to the three-dimensional positions of the respective aircraft, and displays a warning mark when a distance between two aircraft is shorter than a threshold value, wherein the warning mark comprises a triangle having three apexes, which comprise the aircraft marks, and a position that is apart from the aircraft mark of one of the aircraft along a vertical line extending perpendicular to the one aircraft toward a ground surface of the terrain by a distance corresponding to an altitude difference between both aircrafts on the display screen.

Abstract: A display system for a vehicle is provided. The display system includes a display configured to render a representation of an intended vehicle path. At least one relative speed indicator is rendered upon the display. The at least one relative speed indicator is configured to move along the representation of the intended vehicle path, in an area of the display that is peripheral to a focus area of the display, in response to a difference between an actual value of a speed-based parameter and a preferred value of a speed-based parameter of the vehicle.

Abstract: A flat panel display system for an aircraft display includes a graphics rendering computer for rendering of anti-aliased graphical imaging data derived from aircraft sensors for full-field imaging on a cockpit display screen. A comparator processor independently generates, from the same sensor data, a selected subset or “points of light” of the display screen image and compares the points of light data to the data generated by the rendering computer for the same display screen pixel locations. The minimized processing requirements and simplified design of the comparator processor enable ready FAA certification of the comparator processor, whereas the extreme complexity and processing operations required of the rendering computer make FAA certification thereof unusually time consuming and expensive.

Abstract: A system, comprising a data receiving arrangement to receive target data points from a data feed arrangement, each target data point including data corresponding to a location of a target aircraft and additional information on the target aircraft, a data analyzing arrangement to analyze the target data points and store each target data point in a target flight record, the target flight record corresponding to the target aircraft a data generation arrangement to generate a flight track for the target aircraft using the data stored in the target flight record and a data distribution arrangement to organize the flight track and the additional information into a displayable file and distribute the file to users of the system, wherein the displayable file is displayed on a single graphical user interface including the flight track and the additional information.

Abstract: Systems and methods are provided for integrated control, access, and presentation of flight information within the cockpit. Cockpit instrument systems and methods are provided which include a first cockpit instrument panel which has a first display proximately located to a first bezel. The first display is operable to present navigational data, communication data, and flight information data including airspeed, attitude, and altitude. The systems and methods further include a second cockpit instrument panel located adjacent to the first cockpit instrument panel. The second cockpit instrument panel has a second display proximately located to a second bezel. The second display is operable to present navigational data, communication data, and flight information data including detailed engine parameters.

Abstract: A programmable symbology is provided that defines a series of geometric forms in the visual field of a pilot. The symbology includes a virtual representation of a predicted flight path of the aircraft and a virtual representation of a projected contact point with an external object, including the ground. The symbology also provides a virtual representation of a predicted flight path of the aircraft that is projected onto the ground below the projected flight path as a ground path predictor. The symbology further provides a critical slowing air speed indicator.

Abstract: A device for aiding the visual spotting of a second aircraft in flight by the pilot of a first aircraft looking at the sky through the canopy may include an approximately vertical display device and a first device that displays on the display device a representation of the canopy. A communication device receives position information relating to the second aircraft from an outside source. Using the received position information, a second device displays on the display device a symbol representative of the second aircraft such that the position of the symbol in relation to the displayed representation of the canopy corresponds to the position of the second aircraft in relation to the aircraft's canopy as seen through the pilot's field of view.