Various aircraft parameters are sensed by function sensors, the outputs of these sensors being fed to a signal conditioner and evaluator where the signals are processed and the magnitudes of these various parameters evaluated. When the magnitude of any of these parameters is above or below certain predetermined limits, an output signal is fed to a transmitter which transmits a voice message indicating the out-of-limits condition. The occurrence of out-of-limit conditions for any of these paramet...

A combination gyrohorizon instrument for aircraft which visually indicates in addition to the dial display presentation of the instrument, by means of signal lamps appropriately placed with respect to the instrument dial and an audible signal indicative of energization of any one of the signal lamps, departures from straight and level flight that exceed reasonable limits of pitch and bank. The signal lamps, indicating "nose up," "nose down," "left wing down" and "right wing down" are in circuits...

A combination gyrohorizon instrument for aircraft which visually indicates in addition to the dial display presentation of the instrument, by means of signal lamps appropriately placed with respect to the instrument dial and an audible signal indicative of energization of any one of the signal lamps, departures from straight and level flight that exceed reasonable limits of pitch and bank. The signal lamps, indicating "nose up," "nose down," "left wing down" and "right wing down" are in circuits...

An electro-optical aircraft flight instrument that accepts input signals representing angle of attack and pitch angle and used these signals to drive servo reticles which, together with a fixed reticle, are projected at infinity upon a transparent screen in the pilot's normal line of sight. The servoed reticles display flight path of the aircraft and the angle, in degrees, between that flight path and the horizon, while the fixed reticle shows the extension of the aircraft longitudinal axis, or ...

An arrangement for use in a navigating system for a vehicle includes a directional gyro, a heading indicator responsive to the gyro, and a generator for generating a signal during the movement of the vehicle. During movement of the vehicle the reading of the heading indicator is determined by a signal corresponding to the position of the gyro, under the control of a relay responsive to the presence of the generator signal. While the vehicle is stationary this relay switches the small signal due ...

In a system where the aircraft's distance below a radio glide slope is compared with the aircraft's altitude above ground to generate either an advisory voice warning or a command voice warning depending upon the aircraft's altitude and distance below the radial glide slope beam, the repetition rate of the advisory voice warning is varied as both a function of distance below the radio glide slope beam and of altitude in order to generate advisory warnings at a rate reflecting increasing danger t...

Pilot-oriented information is displayed on the screen of a cathode ray tube by electronically generated symbols superimposed on a simulated or real-world picture. The symbology uses as one datum a fixed airplane symbol and locates therefrom the airplane's degree of pitch, degree of roll, and the horizon. In addition, symbols are provided to indicate the relative position of the airplane with respect to ILS localizer and glide slope signals, pitch and roll commands obtained from an on-board fligh...

The circuit is preferably located within an area that is to be secured, is of the type that transmits an ultrasonic signal to establish an ultrasonic wave pattern in the area, and includes doppler phase detection circuitry responsive to both the transmitted and received ultrasonic signals for providing a doppler signal of a frequency corresponding to the velocity of motion in the area. In one embodiment the circuit includes a threshold filter and a detection filter each having different frequenc...

An electro-optical flight instrument is provided which accepts input signals from appropriate sensors and transducers on an aircraft to provide a visual display of the pitch angle of the aircraft, the visual display being established by means of a transparent screen positioned in the pilot's normal line of sight and focused at infinity. A servo reticle is driven in the instrument and is projected at infinity upon the transparent screen, the servo reticle displaying in degrees, the angle between ...

An artificial horizon instrument for an aircraft is described which indicates horizon movements as they would naturally appear to the pilot. The instrument includes a particular support arrangement for the roll ring and pitch ring that permits movements through relatively large angles.