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 energized by a first switching means controlled by the relative rotational position of the inner and outer gimbals of the instrument for sensing departure beyond reasonable safety limits in one direction or the other in the pitch axis, i.e., either "nose up" or "nose down" flight, and a second switch means controlled by the relative rotation position of the outer gimbal and the instrument casing for sensing departure beyond reasonable limits in the roll axis, i.e., either "left wing down" or "right wing down" flight.
This is a continuation, of application Ser. No. 854,633, filed 9-2-69 now abandoned.
This application is a continuation-in-part of U.S. Pat. Application Ser. No. 813,252, filed April 3, 1969, entitled Aircraft Gyrohorizon Indicator With Signal Lamp Positional Attitude Indicating Means.
A system for tactilely alerting an aircraft pilot that the aircraft is in an uncoordinated turn condition and for indicating to the pilot the control adjustments required to correct the turn condition. The system includes a device for sensing the turn condition of the aircraft and a pair of tactile sensation generators in the vicinity of the pilot's legs. The condition sensing device controls activation of one or the other of the tactile sensation generators which indicates to the pilot which foot to depress on the rudder control to return to coordinated flight.
The pilot or crew of an aircraft is alerted to the danger presented by wires in the vicinity of the aircraft by a flight instrument which includes a plurality of wire detected display elements, advantageously arranged as bars on the face of the flight instrument, and which display elements are color coded according to the level of danger presented to the aircraft by the detected wires.
