Abstract: Method and device for assistance with the piloting of an aircraft, especially a transport airplane.

Abstract: Device for reviewing the flight plan of an aircraft, in particular of a transport plane.

Abstract: A self contained electronic system for manual or automatic control and navigation of fixed winged aircraft using electronic position sensing such as GPS, DGPS, WAAS, and the like, as the primary sensor and making use of known flight characteristics of the aircraft to determine aircraft attitude without any interaction with the aircraft, its controls, or the outside environment and without any moving mechanical devices other than switches, dials and connectors. The automatic and visual interface between the system and the pilot provides for simplified flight controls, and a new solution to the hazard of disorientation, and will reduce the time needed for a pilot to become proficient in VFR and instrument flying. A single instrument replaces many of the conventional instruments used for flight. Navigation data is provided in an easy to understand graphical format. The pilot is told explicitly where to move aircraft controls.

Abstract: A system for monitoring the operation of an aircraft, especially a helicopter, includes data acquisition and processing components and display components which are able to display at least one indicator for at least one parameter relating to the operation of the aircraft. The system furthermore includes selection components which allow an operator to select at least one option for a specific configuration of the system, and components able to automatically configure, during the selection of at least one option, at least the data acquisition, processing and display components so as to adapt them to the selected option.

Abstract: A flight data recording system (50) including a flight data recorder (FDR (12) with an integrated flight data acquisition unit (FDAU) (16). The FDR (12) has first and second interface ports for communicating with one or more external aircraft instrumentation subsystems. The system includes an digital communication bus (52) coupled to one of the interface ports and arranged to provide a communications pathway between the FDR (12) and the external aircraft instrumentation subsystems. A portable maintenance access terminal (70) is coupled to the system via a local area network bus (60).

Abstract: An audio signal supplying device for supplying signals to an operating panel for a passenger provided in each of for many seats of a moving vehicle, such as an aircraft or a train, in which the necessity of providing a dedicated adapter or headphone or a device of a complex structure may be eliminated to save costs. The audio signal supplying device has plural operating units for passengers. For example, an operating unit 31 for the passenger has a demultiplexor 12 as a channel selection means for selecting a desired channel and a controller 61 for inhibiting part of channel selection executed by the demultiplexor 12 and for canceling such partial inhibition of channel selection by the demultiplexor 12 in response to a remote control signal received by a remote controlled light receiving unit 91.

Abstract: A system for visually indicating receipt of a radio communication directed to a user having an associated unique identification code. The system includes a radio transponder having an audio output, means for obtaining and storing the unique identification code; a speech recognition circuit operably connected to the radio transponder audio output and the stored identification code; and a visual indicator operably connected to an output of the speech recognition circuit, such that when the stored identification code and said audio input are substantially the same the visual indicator is driven to activation. A method is similarly disclosed.

Abstract: In a process for assisting a user of a motor vehicle in operating components of the motor vehicle, operating conditions of the components are switched by actuating of operating elements. An assistance request element is also provided. Operation of the assistance request element causes a subsequent operation of an operating element only to display information concerning the operating condition which can be switched (in the normal operation) by means of this operating element.

Abstract: An aircraft maintenance tracking system for tracking aircraft maintenance required on an aircraft includes means for tracking accumulated usage data of the aircraft, means for receiving a list of routine tasks required to be performed on the aircraft, means for tracking task accomplishment data for each routine task, means for determining a maintenance due point for each routine task, means for identifying maintenance due tasks as those routine tasks for which a difference between the maintenance due point of the routine task and the accumulated usage data of the aircraft is less than a user-defined critical value, and means for reporting maintenance due tasks.

Abstract: An audio system that may include a flight-worthy electronics package that connects into the airborne electronics of a passenger aircraft, and to that aircraft's passenger system. The audio system may provide passengers with a variety of audio information. The audio information may include a variety of information tailored to phases of the flight plan of the aircraft. Thus, during takeoff, the system may describe the flight plan of the aircraft, whereas during descent, the system may alternately describe the distance to destination and time to destination. Other information that may be described, as desired, may include ground speed, outside air temperature, altitude, time or distance to a point of interest, and points of interest of the area that the aircraft is flying over at any particular moment. The audio system may cause these sequences of descriptions to recite automatically as determined by the preprogramming of the system. Passengers may also be provided with audio destination information.

Abstract: A display system for an airplane or other vehicle is disclosed. A rear projection LCD is used to allow for a maximum amount of screen area to be used in displaying operator pertinent data.

Abstract: A display system for an airplane or other vehicle is disclosed. The system includes a database regarding avionics related data. A method of updating the on board computer database is described.

Abstract: Redundant avionics for flight instruments: a plurality of aircraft flight data sensors, which provide data that are normally displayed on indicators in the cockpit, are transmitted to two independent computers. Each computer is associated with and creates images representative of data sensed by the sensors on a respective projected image display creation device which is in the form of a liquid crystal display, for example. Associated illumination sources and one common or two respective sets of optics project the images from each image creation device on a new screen. The image creation device and the optics would cause the image representative of data from the same sensor to be projected to the same location on the screen regardless of which computer and image creation device provided and projected the image. The computers are independently operable for selectively causing the display of information corresponding to data received from none, some or all of the sensors.

Abstract: A display system for an airplane or other vehicle is disclosed. A rear projection LCD is used to allow for a maximum amount of screen area to be used in displaying operator pertinent data.

Abstract: The present invention relates to a device for aiding the piloting of an aircraft, especially a rotary-wing aircraft, in particular a helicopter. According to the invention, said device (1) comprises first means (2) for determining, on the one hand, the slope and the heading of a preset path of the aircraft and, on the other hand, the slope and the heading of a flight path which the aircraft can take in order to join up with the preset path, and second means (3) for presenting, on a display screen (5), simultaneously a first characteristic sign (S1), whose position on the display screen (5) is representative of the slope and of the heading of the preset path and a second characteristic sign (S2), whose position on the display screen (5) is representative of the slope and of the heading of the flight path.

Abstract: An integrated and dynamic symmetrical display of flight instruments for universal use in aircraft, wherein key instruments indicating with respect to aircraft direction are specifically arrayed with respect to key instruments indicating aircraft rate, wherein flight under instrument flight rules may be more easily learned, undertaken, and practiced with greater safety and ease of pilot workload, as compared with asymmetrical and random conventional flight instrument displays. Specifically, directional instruments are positioned in an aligned row above similarly arranged aircraft rate instruments for quick, reliable pilot scan and information utilization.

Abstract: Indicator of a variable for an aircraft. The indicator (1A) according to the invention comprises means (13) for determining first and second target values respectively of a variable and of its derivative with respect to time, and display means (5, 6, 7) which depict on a display screen (7) a means of indication (14) of the first target value, which is arranged in such a way as to indicate this first target value on a graduated scale (8), and a means of indication (16B) of the second target value which is associated at least with an indicator element (11) indicating said derivative so that, when the latter points toward said means of indication (16B), said variable of the aircraft becomes equal to and remains equal to said first target value and said derivative is equal to said second target value.

Abstract: An airfield hazard automated detection device having a radar for scanning the airfield for obstacles and an automated target recognition system, operably connected to the radar, for comparing the images of the scans of the obstacles to images of known potential hazards and for instructing a directed imaging system to verify the potential hazard by scanning the potential hazard and indicating the result.

Abstract: A method and apparatus for providing passenger selection of meals, beverages, entertainment, and amenity requests from a passenger seat. Additionally, it provides a method and apparatus for providing information to passengers relating to the aircraft flight and position, and information relating to passenger's connecting flights. Such requests and selections are transmitted to a central computer which maintains inventory, and prints passenger requests organized by seat location. The system supervises passenger games, such that a passenger may play a game against the computer, or any combination of passengers can elect to play among themselves. Additionally, while not in active use by a passenger, the system provides for the display of advertising materials on the passenger seat display.

Abstract: A system for voice announcing air traffic controller to pilot data link communication messages of a type which are in conformance with predetermined industry standard message formats, the system and method including a voice annunciation to the flight crew of such messages with the aid of a database of predetermined speech files which correspond to predetermined controller pilot data link communication messages. The flight crew is able to select a language, gender, dialect, accent, etc. of the announced voice message so as to provide for enhanced communication of air traffic control messages to the flight crew.

Abstract: A system for monitoring the operation of an aircraft, especially a helicopter, which automatically provides information which relates to the operation of the aircraft. Data acquisition and processing units centralize data relating to the aircraft together and group them in information pages. At least one information page contains a flight report of at least the latest flight of the aircraft, which simultaneously provides a flight number, flight duration, number of cycles of the engines, number of cycles of the turbine, and any appropriate message regarding detected faults and/or whether any of the aircraft's limitations have been exceeded. A display unit displays the information within the view of at least one pilot of the aircraft. At the end of a flight, a selection unit automatically selects a flight report which is automatically displayed by the display.

Abstract: Accurate, unambiguous, and space-efficient electronic display techniques are provided for presenting the operator with an indicator whose graphical configuration varies in accordance with whether the relevant control value is within a predetermined tolerance range of a set-point value. More particularly, a control value indicator includes a scale having an axis associated with the control value, a set-point marker placed at a first position along the scale for indicating the set-point value, and a pointer having a second position along the scale for indicating the control value. The pointer and/or the set-point marker exhibit a first graphical configuration corresponding to the case where the control value is not within the predetermined tolerance of the set-point value, and a second graphical configuration corresponding to the case where the control value is within the predetermined tolerance of the set-point value.

Abstract: The present invention relates to an indicator for monitoring the path of an aircraft in a horizontal plane, comprising:sensors delivering information relating to said aircraft,means for processing the information delivered by said sensors,means for displaying the signals delivered by said processing means presenting on a display screen:a symbol (11) portraying the position of the aircraft, the extensions of which designate the longitudinal (X--X) and transverse (Y--Y) axes of the aircraft,a compass rose (10) which can move in rotation about said symbol.According to the invention, said compass rose (10) presents a deformation along at least one of said longitudinal (X--X) and transverse (Y--Y) axes.

Abstract: An avionics display unit for use in a flight management system (FMS) of an aircraft, and a method of using the same to increase a pilot's awareness of scheduled changes in operational modes of the aircraft are disclosed. The display unit includes a display device adapted to receive FMS data and to provide a graphical representation of a flight plan for the aircraft relative to a representation of a current position of the aircraft. The display unit is also adapted to provide future mode annunciators, representative of future operational modes of the aircraft, adjacent to positions on the graphical representation of the flight plan at which the future operational modes are scheduled to occur.

Abstract: A laser guidance system includes at least two laser beam generating devices that generate a beam which reflects off a reflective surface positioned on the backside of a propeller blade in order to indicate to a pilot in which direction the aircraft has deviated from a desired flight course. The reflective surface is placed on an area near the tips of the blades of a single engine aircraft propeller to provide a display surface to reflect the laser beam to create a light spot. The laser beam directs light to the left or right side of the nose of the airplane onto the circular path the reflective surfaces made when the propeller spins. The resulting light spots indicate which direction, left or right, a pilot should maneuver the aircraft to follow a desired flight course.

Abstract: An avionics display (10) for use in an aircraft navigation system including a navigation receiver. The avionics display (10) includes a needle (12) for indicating the position, heading, glide slope or other navigational parameter of the aircraft and a stepper motor (14) coupled with the needle and responsive to the navigation receiver for driving the needle in response to the navigation signals received by the receiver. The stepper motor drives the needle at a much higher torque than prior art displays and is therefore less sensitive to contaminates and magnetic interference and is less fragile.

Abstract: A system for detecting cargo movement inside a cargo compartment of a craft, such as a plane or vehicle. The cargo is mounted on pallets that in turn are transported within the cargo compartment on rails end kept in place by latch assemblies. An arm assembly is mounted to a fixed convenient location inside the compartment at its distal end attached to a suitable position on the cargo being monitored. At least two parallel arms are pivotally mounted to the fixed position at the distal end. One of the arms to pivotally mounted indirectly through plate members. The plate member pivotally mounted to the fixed end includes a magnetic element that moves in physical proximity to a magnetic field sensor. If the separation exceeds a predetermined magnitude, the sensor generates an output signal that is transmitted to the pilot or driver for the necessary measures to be taken.

Abstract: A pilot warning system is disclosed for a helicopter having a main rotor rotatable about a yaw axis, a fuselage connected to the main rotor and having a tail boom with a controllable force mechanism to counter-act the torque exerted on the fuselage by rotation of the main rotor. The pilot warning system acts on foot pedals operatively connected to the controllable force mechanism, with the pedal movement controlling the amount of force exerted by the controllable force mechanism on the tail boom to the control the orientation of the helicopter fuselage about the yaw axis. A position sensing device senses the location of at least one of the foot pedals between its first and second positions, and a warning indicator operatively connected to the position sensing device provides a warning to the pilot when the sensed foot pedal reaches a predetermined distance from one of the first and second positions.

Abstract: A two-stage alarm for a rotary wing aircraft, such as a helicopter which operates on a collective control arm. A moveable mass or weight is operatively connected to the collective control arm. The moveable weight may be of a reciprocating type or a rotor driven mass which is mounted eccentrically for rotation about an axs which is spaced from the center of gravity of the weight. In the latter case, a D.C. motor spins the weight rapidly about the axis at a first speed to produce a shaking action to the collective control arm as a warning of an approaching danger. The weight is moved more rapidly to produce a much more noticeable action at a second frequency, or at an increased amplitude as a warning of a more imminent or serious condition which requires immediate action.

Abstract: A novel intelligence support of an aircraft crew and the like employing videocards with pictogram signs indicating corrective action to be taken by the crew for emergency flight situations and monitoring the achieving of such corrective action.

Abstract: A liquid crystal display flight indicator unit having the capability to display a horizontal situation indicator (HSI) or an attitude direction indicator (ADI) on the viewing area of the same unit. Signals from existing aircraft electronics are processed to determine whether the incoming signal is an HSI or ADI graphical image to be displayed on the viewing area. A unique component layout is described to enable HSI and ADI to be contained within a unit having a chassis size not larger than previously known HSI and ADI units.

Abstract: The present invention relates to an aircraft flight indicator intended to supply a data item regarding the power margin available on at least one engine of the aircraft as a function of the flight conditions. According to the invention, the indicator comprises: a sensor (2) capable of delivering data relating to the speed (Ng) of the gas generator of the engine; means (3) for calculating, using the data relating to the speed (Ng) of the gas generator, a data item .DELTA.Ng representing the difference between the actual value of Ng and the reference value on take-off and for processing said data so that it can be displayed; and display means (4) showing the data relating to the values of the speed Ng of the gas generator and/or of .DELTA.Ng on a display screen (5).

Abstract: An embedded mission avionics data link system is provided which allows an aircraft to receive, transmit, and process a variety of different types of information. The present system has the capability of generating and receiving video information for viewing by a pilot in the cockpit. The system also requests, receives and recognizes situation awareness data as well as mission update data and processes this information accordingly. Any video images received by the pilot either externally or internally may be annotated and either stored in memory or transmitted externally. The system allows multiple aircraft on a mission to stay in constant communication as to relative positions to each other and targets, provide up-to-date information as to the situation which exists at the target, and do this in a mostly automatic fashion which reduces the workload of the pilot and significantly enhance the mission capability.

Abstract: A method and apparatus using a simplified language consistent with air traffic control syntax for inputting, displaying and controlling the operation of a flight management system of an aircraft to comply with the instructions received by the pilot from the air traffic controller.

Abstract: A device for monitoring a complex system includes a central unit for transmitting monitoring information to a display unit, the display unit displaying messages concerning the information received. The central unit is loaded with a database containing additional information. At the time of transmitting monitoring information it indicates the existence of additional information. The display unit displays a signal indicating the existence of the additional information.

Abstract: An apparatus (700) for inhibiting operation of an electronic device (702) during take-off and landing of an aircraft (802) has a sensor (704) that measures a lateral acceleration. A control circuit (706) is coupled to the sensor (704) and has an output (708) coupled to the electronic device (702).

Abstract: A device to control an aircraft system in manual pilot mode, using notably a head-up display, is constituted by a display screen located at the position of a piece of equipment of the right-hand part of the instrument panel, the screen displaying information elements delivered by the replaced equipment and information elements to control the piloting task. Application for the controlling of a manual pilot phase by a co-pilot in an aircraft using a head-up display.

Abstract: A fuel time indicator which is removably mountable about a fuel tank selector switch for monitoring and displaying tank usage times for each of a plurality of fuel tanks is disclosed. The fuel time indicator comprises a portable frame including a switch position sensor for monitoring a plurality of positions of the fuel selector switch and generating a corresponding switch position signal. A timer generates a timing signal indicative of elapsed time. A controller responsive to the position signal and the timing signal generates tank usage times for each of the fuel tanks by selectively aggregating elapsed times. Visual indications of the tank usage times are provided by a display.

Abstract: A method for preparing and controlling navigation of an aircraft uses a processor equipped with memories, a screen and keys. It comprises the steps of preparing the route to be followed by an aircraft by loading into the memory data pertaining to a route, defining parameters characterizing the environment in which the navigation will take place, and displaying during navigation a couple of way points including the last point through which the aircraft has passed and the next way point, the segment joining these two points together, and information required to control navigation between these two points. The invention enables the pilot to prepare his navigation without taking measurement readings and performing calculations.

Abstract: A novel intelligence support of an aircraft crew and the like embodying videocards with pictogram signs indicating corrective action to be taken by the crew for emergency flight situations and monitoring the achieving of such corrective action.

Abstract: An ambiguous dial indicator intuitively communicates the relative value of setpoints to an operator. The ambiguous dial indicator includes an ambiguous scale and a pointer or needle. The setpoints are represented by "bugs" which are adjacent to the ambiguous scale. The bugs are limited to a predetermined range about the pointer such that when a setpoint is outside of the predetermined range the associated bug is limited to an edge of the range. When several setpoints are outside of the predetermined range the several associated bugs saturate or park at the edges of the range. The invention is particularly useful in head-up displays and helmet mounted displays.

Abstract: A liquid crystal display flight indicator unit having the capability to display a horizontal situation indicator (HSI) or an attitude direction indicator (ADI) on the viewing area of the same unit. Signals from existing aircraft electronics are processed to determine whether the incoming signal is an HSI or ADI graphical image to be displayed on the viewing area. A unique component layout is described to enable HSI and ADI to be contained within a unit having a chassis size not larger than previously known HSI and ADI units.

Abstract: This optoelectronic device is designed to provide assistance in the piloting of an aircraft under conditions of poor visibility, at the final approach stage, during taxiing and at take-off from a runway equipped with an ILS. The device consists of a collimator displaying a reticule symbolizing a runway centerline that is shown to the pilot during flight as well as on the ground, without any break between the in-flight final approach stage and the ground stage of taxiing on the runway. The device takes account of the pilot's off-centered position in the aircraft cockpit.

Abstract: The disclosed optoelectronic device is designed to facilitate the piloting of an aircraft under conditions of poor visibility, notably during landing at the stage when the aircraft approaches a runway. It consists of a collimator which displays, in addition to the artificial skyline, miniature aircraft index and attitude bars, a slope scale positioned across and on either side of the artificial skyline, at the position of the selected course chosen by the pilot. This slope scale, depicted in the form of a line of dots spaced out at one slope degree, enables the pilot to be presented simultaneously with information on selected course and slope and enables the determining of pitch attitude with high precision.

Abstract: A new aircraft cockpit instrument panel display system for showing the operating status of different aircraft systems is disclosed. The color display includes a plurality of display segments. Each display segment combines trend qualitative information of the direction of movement of aircraft system parameters, categorical qualitative information of whether aircraft system parameters are inside or outside acceptable ranges, and quantitative information of the actual level of aircraft system parameters. Trend information is indicated by an analog dial display element having a moving needle to indicate rising, falling or constant values of the parameter. The dial display also includes peg positions to indicate that the value of a system parameter has "pegged" at its lowest or highest value. Categorical qualitative information is indicated by the color of the dial, generally green for safe values, yellow for cautionary values and red for danger values. Quantitative information is indicated by a digital indicator.

Abstract: A system and method for detecting and viewing aircraft hazardous incidents such as flying aircraft and meteorological phenomena which includes microbursts, thunderstorms, tornadoes, and the wake turbulence of aircraft. The aircraft hazardous incidents are positionally and horizontally displayed to the pilot on a display, that is located in the aircraft cockpit, in relation to the flight path of the aircraft. The timely displaying of any of the aircraft hazardous incidents permits the pilot to take evasive action to avoid a potentially dangerous incident.

Abstract: A maintenance interval indication system, apparatus and method are provided that are cost-effective for general aviation aircraft and that may be retrofitted to existing airplanes. The system includes an on-board aircraft cycle counter and engine run-time and flight time logging instrument that requires no external transducers, no electrical signal inputs and only a single electrical power input from an airframe's electrical system. A microprocessor in the engine cycle logger accepts data input from an acoustic transducer and from a pressure transducer (i.e., altimeter), and correctly logs engine cycles in spite of factors such as: a) touch-and-go landings; b) in-flight engine shutdowns; c) noise from another engine on the same aircraft: d) wide variations in acoustic input levels from one engine to the next; e) changes in acoustic level following an overhaul of the monitored engine; f) transient noise artifacts; and g) transient altitude artifacts.

Abstract: A method for assisting the piloting of an aircraft from a voluminous set of memory-stored documents which uses a processor associated with a terminal comprising a screen and control and data entry keys and with memories containing useful information for operating a flight, the processor being connected to other items of equipment of the aerodyne. The method comprises storing of information in a data base and supplying first exploitation functions of this information, real-time acquisition by the processor of an event relative to the current situation of the aerodyne and analyzing the new situation generated by the occurrence of this event, preselecting the information in the data base best adapted to the new situation, and classifying same by order of relevance, supplying second exploitation functions of the preselected information, selection and exploitation, by the operator, of one of the exploitation functions. The method applies in particular to the civil and commercial aviation.

Abstract: The invention describes a liquid crystal display having an enlarged viewing area by moving the liquid crystal glass from the chassis portion of the assembly to the bezel portion of the assembly. In one preferred embodiment the viewing area of a horizontal situation indicator on an aircraft instrument panel may be increased by fifty percent or more.

Abstract: A method and apparatus provides instantaneous passive range measurement oard an aircraft for determining the range between the aircraft and a target. The target may either be stationary or a slower moving vehicle. Calculation of the desired range is achieved using the formula: Range=(S/S')V(Cos a)(Cos b) where "S"=apparent target size; "S'"=rate of change of apparent size; "V"=ground velocity; "a"=azimuth angle from aircraft heading to target; and "b"=elevation angle from the aircraft heading to the target. The apparatus consists of an automatic video tracker, a video camera, and a servo controlled aiming platform. The video tracker provides target size data. Resolvers on the aiming platform are utilized to determine the azimuth and elevation angles from the aircraft axis to the target. The azimuth angle is added to the aircraft drift angle to determine the total azimuth angle from the aircraft heading to the target. The drift angle and ground velocity are obtained from the aircraft inertial system.