GB576359A - Improvements in or relating to controlling aircraft - Google Patents

Abstract

576,359. Gyroscopic apparatus. MEREDITH, F. W., and GARDNER, G. W. H. Oct. 27, 1938, No. 31132. [Class 97 (iii)] [Also in Group XXIX] In an aeroplane, a sight is stabilised to the vertical during banked turns by rotatably mounting the sight about an axis in the plane of symmetry of the aeroplane not coincident with the yawing or vertical axis of the aeroplane, and when a turn is required, the sight is rotated thus giving an indication to a human pilot, or being communicated to an automatic pilot, and the aeroplane is turned at a rate depending on the extent of the original movement of the sight. As shown, the arrow g, Fig. 1, indicates the direction of flight, and the sight 2 can be rotated about an axis 3 by means of a flexible cable from a control handle 4. Movement of the latter varies the spring loading pressure-regulating valves 17, Fig. 2, interposed in an air pressure line 14 which leads through conduits 15, 16 to a servopiston 5. The differential pressures obtained from movement of the control handle act on the piston 5 which through a lever 6 moves the inner gimbal ring of a gyroscope and causes the latter to precess. The fulcrum 7 of the lever 6 is adjustable to allow for different flight speeds, and if the setting is indicated airspeed, compensation for the effect of density on rotor speed is obtained. The gyroscope is mounted on a support 1 and has 3 degrees of freedom to measure directly a function of the deviations is azimuth and roll. Movement of the outer gimbal ring actuates a valve b controlling a servo-piston c connected to the ailerons through a lever h. A follow-up effect is obtained from a lever d. An anti-topple device comprises a valve e actuated from the inner gimbal ring and controlling a servo-piston f connected to the outer gimbal ring.