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 and on the earth's surface, or a slower moving vehicle. Calculation of the desired range is achieved using the formula: Range=[Sin a/Sin b] V; where "a"=angle from aircraft heading to target, "b"=turning rate; and "V"=ground velocity. The apparatus consists of an automatic video tracker, a video camera, and a servo controlled aiming platform. A resolver on the aiming platform is utilized to determine the angle from the aircraft axis to the target. This angle is added to the aircraft drift angle to determine the total angle from the aircraft heading to the target. The video tracker is utilized to determine the turning rate of the aiming platform.

Abstract: A maneuver envelope warning system for an aircraft having operating limits, operating condition sensors and an indicator driver. The indicator driver has a plurality of visual indicators. The indicator driver determines a relationship between sensed operating conditions and the operating limits; such as, a ratio therebetween. The indicator driver illuminates a number of the indicators in proportion to the determined relationship. The position of the indicators illuminated represents to a pilot in an easily ascertainable manner whether the operational conditions are approaching operational limits of the aircraft, and the degree to which operational conditions lie within or exceed operational limits.

Abstract: An aircraft display system has a display unit comprising a matrix array of LED's mounted in the glareshield. Air traffic command signals received by a datalink processor produce a visual indication on the display unit which is visible to the pilot when looking through the window. A button on the display unit is pressed by the pilot to acknowledge receipt of instructions. Other important messages are displayed by the display unit at different times. Radar altimeter height is displayed in a color which changes when the aircraft descends below its flare height. When on the ground, the display unit displays alphanumerically the distance-to-go to the end of the runway, and simultaneously displays stripes that move horizontally to indicate deviation of the aircraft from the runway center line.

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: An improved method and apparatus for drawing energy management circles on electronic flight instrument system displays which includes a microprocessor for making several initial inquiries regarding the orientation of the circle with respect to the display and issuing write or don't write commands for each point on the circle without the need for individually analyzing each point as to whether it is located on the display screen.

Abstract: A digital information storage and read-out system in which digital elevation and cultural terrain data is read from a magnetic tape in compressed form into an intermediate memory which operates as a speed buffer memory. The data in the intermediate memory is read out to a reconstruction processor in which the compressed data is reconstructed and applied to a scene memory. A navigation computer determines the instantaneous position of a vehicle with respect to the terrain and controls the reading of data into the scene memory in blocks with the vehicle position occupying a center of scene location. In order to provide a heading up display of the terrain, the data in the scene memory is raed out at an angle to its north-up storage orientation and interlaced scanning of pixel data in the scene memory improves resolution and enhances line display.

Abstract: A gyroscopically stabilized artificial horizon instrument used in light aircraft mounts an earth magnetic field sensitive flux sensor on its gyroscope housing to produce a signal indicative of the direction of flight. The signal is processed and produced as a digital display of direction on the face of the instrument such that the planes relation to the artificial horizon and its direction can be observed by the pilot at the same instrument location. Provision is also made for generating signals indicative of airspeed and altitude and displaying in digital form both airspeed and altitude at the same location on the artificial horizon instrument at which direction is displayed.

Abstract: A lap top navigation instrument, suitable for aircraft, includes a chart compartment covered by a transparent window containing a liquid crystal display as part of the window through which a conventional map or chart in the compartment can be viewed and a computer whereby an image can be generated in the display above the chart in the compartment and, through inputs to the computer from the aircraft's instruments, the computer generated image in the display will be continuously repositioned above the surface of the chart so as pilot using the device has a continuous visual indication of the position of his aircraft over the topography depicted on the chart in the compartment. Directional components may be added to the image giving the pilot additional information in reference to the heading of the aircraft relative to the chart's display of "North" showing how the image is actually tracking over the chart in the compartment.

Abstract: A method of and apparatus for determining the actual lateral deviation from the centerline of a runway of an aircraft located outside the normal region covered by a glideslope beam is disclosed. The method comprises the steps of scaling a geometrically developed estimated lateral deviation value (Y.sub.estimate) with a compensation factor (K) and passing the result through a complementary filter. The complementary filter produces an estimated lateral deviation rate value (Y.sub.estimate) that is divided into the actual lateral deviation rate value (Y.sub.actual) produced by the inertial navigation system of the aircraft. The result of the division is the compensation factor (K) that is used to scale the geometrically developed estimated lateral deviation value. Preferably, the compensation factor is filtered by a first order lag filter prior to being used to scale the geometrically developed estimated lateral deviation value.

Abstract: The display device of the invention includes several flat screens. Two sides of a case each form a flat screen display face controlled by the same control system. Under normal operation, the case is held in slides and only the screen disposed on one side is visible and in the emergency mode the case is pulled out of the slides and is pivoted so as to cause the other screen disposed on the othr side to appear.

Abstract: A display unit has a transparent front panel one surface of which carries reflective markings that are illuminated by internal reflection in the panel from edge-mounted bulbs. Behind the panel are located light-emitting display devices such as provided by LED's. Illumination from the bulbs is controlled by manually adjusting a rheostat 36. The brightness of the display devices is controlled by means of two photodiodes. One photodiode responds to the level of ambient light falling on the front panel; the other photodiode is shielded from ambient light and responds to light from an additional bulb connected in parallel with the edge-mounted bulbs and having the same illumination characteristics. The brightness of the display devices is thereby automatically decreased when ambient light levels fall and increased when the markings are brightly illuminated, so that they are not masked by bright markings.

Abstract: The rate-of-climb indicator of this invention can indicate the existence of wind shear.

Abstract: As a method and device for representing the horizon on board an aircraft, there is displayed on the cathode tube of a collimator an image comprising a circle of small size inside which there are, on the one hand, a horizon line inclined to the horizontal by an angle equal to but opposite the rolling angle of the aircraft, the horizon line being remote from the center of the circle by a distance which is a function of the pitching angle in the upward direction when the aircraft is diving and in the downward direction when the aircraft is pulling the nose up, and which delimits to zones of different brightness and, on the other hand, a point representing a pole situated on the median line of the horizon line at a distance from the latter corresponding to a pitching angle of 90.degree.. A "head up" type control system is essentially provided.

Abstract: On board functions are performed in an aircraft with the aid of a central control computer connected to a plurality of input and output devices including data terminals for passengers and flight attendants, through a data bus system and through decoder/encoder units linking the data terminals to the data bus system for providing an operation with digital signals. Thus, digital signals are transmitted back and forth between the central control computer and the data terminals in such a way that computations initiated on a data terminal are performed by the central control computer and so that the computation results and any other information are displayed on a display field forming part of the data terminals, one of which is provided at each passenger seat. Modified terminals are provided at various other locations within the aircraft cabin for use by a flight attendant.

Abstract: A turn-and-bank indicator can integrate with regard to time the displacement of a pointer of the turn-and-bank indicator, the pointer indicating the turning rate of the airplane. It includes a non-contact converter which outputs an electrical signal in proportion to the deflection of the pointer; an amplifier which amplifies the output of the non-contact converter; an integrator which integrates the output of the amplifier with respect to time; and a digital display unit which displays the output from the integrator at a close position with the pointer.

Abstract: An aircraft control position indicator is provided that displays the degree of deflection of the primary flight control surfaces and the manner in which the aircraft will respond. The display includes a vertical elevator dot/bar graph meter display for indicating whether the aircraft will pitch up or down, a horizontal aileron dot/bar graph meter display for indicating whether the aircraft will roll to the left or the right, and a horizontal rudder dot/bar graph meter display for indicating whether the aircraft will turn left or right. The vertical and horizontal display or displays intersect to form an up-down-left-right type display. Internal electronic display driver means receive signals from transducers measuring the control surface deflections and determine the position of the meter indicators one each dot/bar graph meter display.

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 G-force acceleration measuring instrument for use in an aircraft, spacecraft, submarine, or other vehicle, and employing electronic sensing and display transducers for increased reliability, small size, and small mass. The instrument includes a bar graph display, preferably incorporating liquid crystal transducer elements, uses a solid state or limited motion acceleration transducer, and provides graphic and numeric indication of the present G-force value together with numeric indication of historic maximum and minimum G-force values. The instrument also includes gain adjustment arrangements for accommodating different instrument panel slopes mounting in different types of vehicles with different G force capability, and a signal output tap for recording or slave indicating or telemetry or feedback use.

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: In order to provide an aircraft navigation computer display unit for use in an aircraft with limited cockpit panel space, the display unit is provided with a housing configured in a rectangular cross-section and includes a cathode ray tube assembly secured in an upper quadrant of the housing, a power supply secured directly below the CRT assembly and a group of circuit boards vertically orientated in the remaining half of the housing in tracks that permit the removal of the circuit boards from the front of the housing. The display unit also includes a front panel assembly having data entry and function switches enclosed therein and an opening aligned with the CRT. The front panel additionally includes a plastic filter secured to a shoulder of the front panel assembly in front of the CRT wherein the filter is located approximately 0.010 inch from the CRT when the front panel is secured to the housing.

Abstract: A liquid crystal display (LCD) system and technique is disclosed which enables an improved visual presentation and display of the rate of change of an aircraft parameter in an avionics system. The rate of change of the parameter is computed and its magnitude is used to generate a frequency proportional to that magnitude. The generated frequency is coupled to control circuitry which energizes a plurality of display elements to sequentially and cyclically produce a visual display of those elements at a repetition rate proportional to the generated frequency. The display elements are separated into two groups, one of which indicates the rate of change during one condition of the parameter, and the other of which indicates the rate of change during another condition of the parameter. The display elements are located in groups above and below a digital display of the aircraft parameter. In this manner, the rate of change of a given parameter can be easily perceived even with peripheral vision.

Abstract: Display for use on propeller driven aircraft comprised of a radially disposed row of lamps 12 embedded in the rear surface of a propeller 11. Measurements of flight data are made by conventional means and converted into digital signals (15 and 18). These digital signals are applied to graphic generators, 16 and 19, which control lamp drivers 13 which in turn control lamps 12 through slip rings 14. The lamps 12 are lit at appropriate times (determined by sync pulses 17) during each revolution of the propeller to cause the flight data in graphic form to appear to the pilot.