Abstract: The invention relates to a process for the display on a screen on board an aircraft of flying aid symbols. On the basis of information supplied by an inertial system and ground beacons processed by an on board computer, the process consists of displaying on an on board screen (EV) symbols more particularly representing the wings of the aircraft (A1, A2), the model of the aircraft (CP), its speed (V), the tendency to acceleration and deceleration (AD1, AD2), a flight path prediction (PT), the artificial horizon (H), the roll angle (.phi.), the sideslip (AL) and the total energy (ET1, ET2). It also consists of displaying the flight path to be followed in perspective (P1, P2, S3, S4, S5) and in projection (S'1 to S'5) on the plane of the runway. Any flight path segment during passage, as well as the segment following the latter are displayed in parallelepipedic form (P1, P2) in perspective.

Abstract: Displacements of connecting rods (55) between control devices and control surfaces (10) manipulated by a pilot (8), a pulse data based on the normal pulse of the pilot (8), and time data of the related information are indicated on a central display unit (30) arranged on an instrument panel (9) together with various gauges; a view of instrument panel (9) including a displayed data on the central display unit (30) is captured by a first television camera (20) disposed in a cockpit (6) as a first piece of image information; the actual state of a main wing (2) and that of tail stabilizer (3) reflected on mirrors (22,23) installed on the middle part of the upper fuselage are captured by a second television camera (21) installed on a vertical stabilizer (4) facing the nose of the fuselage as a second piece of image information; and both pieces of image information from respective camera are synchronized and combined as complex image information and recorded on magnetic tape through a video recorder (24).

Abstract: A moving altitude tape for a flight instrument display adapted to provide intuitive visual cues for determining deviation from a desired altitude. A window incorporates a digital altitude readout and a pointer index which is aligned with calibration marks on the altitude tape. In use the tape exhibits a motion in accordance with deviations in altitude of the aircraft and displays a vernier indication of such deviations with respect to the reference index. The tape further includes indicia associated with the reference index for defining predetermined increments of altitude deviation in accordance with commonly commanded altitudes, and a further pointer indicative of actual altitude deviation from a preset altitude.

Abstract: An airplane pitch guidance control law and display symbol for a Traffic alert and Collision Avoidance System (TCAS) is disclosed. The control law converts a TCAS computer-generated vertical air speed command into a pitch guidance command. The pitch guidance command controls the location of a symbol (51) on the pitch axis of an electronic attitude display (21) that guides a pilot toward a pitch attitude that will result in a vertical speed that eliminates a collision threat. The preferred symbol is a pitch axis leg (53) and a pair of outwardly diverging legs (55a, 55b). The pitch axis leg (53) defines the minimum climb or descent attitude required to achieve a safe climb or descent angle. The pitch axis leg (53) and the diverging legs (55a, 55b) combine to define a climb or descent attitude range to avoid. The distance between the pitch axis leg 53 and the boresight 39 of the airplane symbol of the display is controlled by a RA.sub.CMD signal produced by: subtractively combining the vertical speed command (V.

Abstract: The invention relates to a process for the visual display of the attitude of an aircraft to assist piloting or flying in space. On the basis of the values of cardan or gimbal angles (.psi., .theta., .phi.) of the aircraft marked in a reference mark linked with the celestial cavity or firmament and on the basis of a calculation of quaternions, the process consists of displaying on a screen (1) on board the aircraft, in particular the following informations: a cruciform reticule (7,8,9), a piloting or flying circle B, the value of the roll angle (.phi.) in a scale (10), a net formed by portions of meridians (M) and parallels (P) of the celestial cavity, a symbol (V1) representing the direction pointed by the velocity vector of the aircraft, a short term prediction vector (12) for the aircraft attitude, as well as numerical values (19,21,23) for the roll, pitch and yaw velocities. Application is to the piloting of an aircraft in space.

Abstract: A flight-worthy electronics system connecting the airborne electronics of a passenger aircraft to the visual display system of the aircraft provides passengers with a variety of information tailored to phases of the flight plan of the aircraft. For each phase of the flight plan, a different sequence of information is displayed. Thus, for example, during takeoff, the system may display a map showing the flight plan of the aircraft, whereas during descent, the system may alternately display the distance to destination and time to destination. Other information that may be displayed, as desired, is outside air temperature, altitude, and time or distance to a point of interest. The system causes these sequences of displays to appear automatically as determined by the preprogramming of the system.

Abstract: A power management symbology (PMS) display system for helicopters that provides a continually updated, combined analog/digital symbolic display of selected status information vis-a-vis the helicopter powerplant. The PMS display system includes a multi-dimensional, continuously updated, combined analog/digital display symbol that is optimized for discriminability and compatibility with respect to the pilot's visual system.

Abstract: A flight-worthy electronics package that connects into the airborne electronics of a passenger aircraft and to that aircraft's passenger visual display system provides passengers with a variety of information real-time displays. Information that may be displayed, as desired, is flight information such as ground speed, outside air temperature or altitude. Other information that may be displayed is a map of the area that the aircraft is flying over at any particular moment. Perhaps most useful to the passengers is destination information. Besides being able to display a chart of the terminals with all its aircraft gates, and identifying the gate at which the aircraft will be arriving, connecting flight information listing flight numbers, times, gates and destination may be displayed in conjunction with the terminal chart. A flight-worthy electronics package causes these displays to appear automatically on a real-time basis as determined by the programming of the system.

Abstract: A gyroscopic artificial horizon comprises a gyroscope suspended in a gimbal ount which has an inner frame and an outer frame pivoted, one within the other, about two orthogonal axes. It also comprises a device for sensing the spatial position of the axis of the gyroscope and for displaying this position in the form of an artificial horizon. To simplify the mechanical structure and to increase the reliability of the gyroscopic artificial horizon, the device for sensing and displaying the spatial position of the gyroscope axis comprises a luminous display screen rotationally coupled to the outer frame of the gimbal mount. It further comprise a sensor for sensing the angular position of the inner frame relative to the outer frame and a processor device adapted to display this angular position on the screen in the form of an artificial horizon.

Abstract: A combination indicator apparatus including an indicator assembly having plural analog indicators of the same type for independently indicating different information, plural driver circuits of the same type for independently driving the analog indicators; and a single controller containing a CPU and an instruction set, which controller may be disposed remote from the indicator assembly, for receiving various sensor information and transmitting various drive data to the driver circuits in time sharing data transmission mode, to independently indicate various information through the analog indicators.

Abstract: An integrated avionics control and display arrangement is disclosed which combines symbol generation, display and mission processing, and multiplex bus control in a single processor configuration. The arrangement features "home" pages for primary parameter display with selectable additional pages available in conjunction with operator-operable keys disposed around the display. A wide variety of control signals compatible with the multiplex bus format are integrated directly with the bus, and a wide variety of non-compatible signals are integrated with the bus through remote terminal units which are arranged in a redundant configuration for system failure survivability and enhanced interconnect wiring economy.

Abstract: An indicator monitor which performs a plurality of functions. Both engine exhaust gas temperature and engine rpm are monitored. Based on the engine rpm, it is determined whether the engine is in starting or operating condition. Different parameters and different values are used based on this indication. A plurality of different functions including parameters indicative of temperature in rpm can be monitored by this one meter with a single display and which has electronics that can be housed in an area smaller than the display face.

Abstract: The invention relates to a status display system for aircraft which system receives signals from sensors/transducers monitoring a plurality of parameters and subsystems of the aircraft. The system then displays text identifying faulty ones of the parameters or subsystems in a prioritized sequence. With the system of the invention, only a single indicator is needed to identify a plurality of faults as compared to available systems wherein each parameter and subsystem is monitored by a separate device including a separate display. Thus, the present invention is an improvement over the prior art in that: (1) it requires less cockpit space for displaying faults, and; it presents faults in order of priority so that the pilot does not have to make decisions about the most important fault to attend to when, as in the prior art systems, faced with a plurality of fault indications on a plurality of fault indicators.

Abstract: An aircraft attitude display device comprising: a circular array of radially extending selectively activatable display elements (5), the radially inner ends of which constitute a boundary defining a central space; within the said central space, a fixed aircraft symbol (7); and means for selectively activating the said display elements in accordance with aircraft attitude so that the selected display elements form a visible pattern, e.g. a sector of the array, bearing a geometrical relationship with respect to the aircraft symbol indicative of the aircraft attitude.The device is suitable for implementation using liquid crystal display technology to give a stand-by display of aircraft pitch and roll which is readily understandable by pilots since it is similar to the display given by conventional rolling ball action aircraft attitude instruments.

Abstract: A self-contained, standby flight instrument includes sensors, processing circuitry, rechargeable power supply, voltage regulation circuitry, and display hardware arranged to provide a continuous display of aircraft airspeed, altitude, roll, pitch and heading regardless of any partial or complete failure in the primary instrumentation, an interrelated subsystem, or the electric power supply.

Abstract: A solid state attitude and director indicator (ADI) is disclosed utilizing liquid crystal display technology to represent attitude of a vehicle in two axes. A visual representation of attitude changes is provided on the liquid crystal display as well as numeric data, in a preferred embodiment. Additionally, glideslope, localizer, and approach speed may be displayed as well as heading and command bar information.

Abstract: A system for providing a Head-Up Display (HUD) on board an aircraft to assist a pilot in guiding the aircraft. The display is positioned in the pilot's normal line of sight. In one mode it utilizes a radio beam landing system such as an ILS (Instrument Landing System) to generate symbols that correspond to visual ground cues which, together with an aircraft symbol display, provide the pilot with cues for aligning the aircraft on the appropriate path for approach and landing. The system moves the aircraft symbol in accordance with motion changes of the aircraft. During a landing approach the pilot "flies" the aircraft symbol relative to the simulated and/or real ground cues. By making the HUD correspond with ground cues, the abrupt transition from instrumented to visual flight is eliminated. At altitudes below which available ILS is not acceptable, the system provides a smooth transition to a mode independent of ILS and then to a flare mode.

Abstract: A system for providing a Head-Up Display (HUD) on board an aircraft to assist a pilot in guiding the aircraft. The display is positioned in the pilot's normal line of sight. In one mode it utilizes a radio beam landing system such as an ILS (Instrument Landing System) to generate symbols that correspond to visual ground cues which, together with an aircraft symbol display, provide the pilot with cues for aligning the aircraft on the appropriate path for approach and landing. The system moves the aircraft symbol in accordance with motion changes of the aircraft. During a landing approach the pilot "flies" the aircraft symbol relative to the simulated and/or real ground cues. By making the HUD correspond with ground cues, the abrupt transition from instrumented to visual flight is eliminated. At altitudes below which available ILS is not acceptable, the system provides a smooth transition to a mode independent of ILS and then to a flare mode.