GB196296A - Improvements in pitch indicators particularly for aircraft - Google Patents

Abstract

196,296. Sperry Gyroscope Co., (Assignees of Sperry L. B.). April 14, 1922, [Convention date]. Gyroscopic apparatus.-Apparatus for indicating the angular velocity of an aircraft &c. around its transverse horizontal axis comprises a gyroscope the rotor 10 of which rotates on a spindle 12 parallel to the longitudinal axis of the craft, the spindle being mounted in bearings 13 in a ring 14 which is mounted in bearings 20, 21 in a casing 23 so as to be capable of precession about its vertical axis in response to rotation of the aircraft &c. about its transverse horizontal axis. The precession is opposed by a spring 25 extending between the ring 14 and an adjustable spring member 26 on the frame 23, and is transmitted to a pointer 32 by a closely-coiled spring 40 attached to the ring 14 and to one arm 41 of a bell-crank, the other arm 43 of which has a pin 44 engaging the forked arm of a lever 45 mounted on a spindle 33 to which the pointer is secured. Movement of the lever 45 is opposed by a spring 46. By making either of the springs 25, 46 of sufficient strength the other spring may be omitted. To permit the rotor 10 to be driven by air the frame 23 can be enclosed in an airtight casing 50 from which air is withdrawn by a Venturi tube on the craft, the air so withdrawn being replaced by air entering through a nozzle 58 in the bearing 21 and impinging on buckets 11 on the rotor.