GB411921A - Improvements in navigating instruments for aircraft - Google Patents

Abstract

411,921. Gyroscopic apparatus. BENDIX AVIATION CORPORATION, 401, Bendix Drive, South Bend, Indiana, U.S.A. Dec. 17, 1932, No. 35833. Convention date, Dec. 19, 1931. [Class 97 (iii).] A deviation indicator, particularly for indicating pitching and azimuth deviation of aircraft, comprises a gyroscope rotatable on a universally supported non-rotatable shaft and automatic centralizing means independent of the gyroscopic element and the driving means therefor. In the form shown, the rotor 7 is mounted by roller bearings 10, 11 on the shaft 9 which has a funnel shaped extension 20 pivoted at 21, 22 to a gimbal 18 pivoting in turn on a member 17 secured to the air-tight casing 4. Air is drawn from the casing by the Venturi tube 14 and nozzles 12, 13, co-operating with buckets 8 on the rotor, are provided in the walls of the casing. Relative inclination between the gyro axis and casing 4 is indicated by a pointer 24 secured to the shaft 9 and co-operating with a dial 25. In order to return the gyro slowly to the central position after deflection the shaft 9 is provided with two pairs of fixed vanes, e.g. 31, 32, associated with jets, e.g. 41, 40. Inclination of the gyro axis brings one (or more) of the vanes into the air stream of the corresponding jet and produces a torque precessing the gyro back to the central position. The jets 41, 40 may be controlled by a valve or replaced by jets of a different size. The pointer 24 is provided with a collar 55, having a limited rotation thereon against the action of the spring 58 and provided with pins 51 adapted upon undue inclination of the gyro axis to engage rack teeth on the inner edge of a frame 48 enclosing the pointer 24. For quickly centralizing the gyro a plunger 63 may be depressed, causing a spring urged rod 59 to engage the funnel member 20.