GB1071371A - Improvements relating to gyro-stabilised platforms - Google Patents

Abstract

1, 071, 371. Gyroscopic apparatus. BODENSEEWERK PERKIN-ELMER & CO. G.m.b.H. Jan. 28, 1965 [Feb. 8, 1964], No. 3829/65. Heading G1C. A stabilized platform 50 having three stabilizing gyros 78, 80, 82 is mounted in three gimbals, an inner roll gimbal 52, a pitch gimbal 56 and an outer roll gimbal 60 to prevent gimbal lock, the inner roll gimbal 52 and pitch gimbal 56 being maintained perpendicular to each other by means of an angle pick-up 80 controlling a follow-up motor 74, a micro-switch (not shown) being provided on the outer roll gimbal 60 to be actuated whenever the angle between this gimbal 60 and the pitch gimbal 56 approaches a right angle, the micro-switch controlling the motor 74 to give prompt turnover of the outer roll gimbal 60 and prevent precession and other disturbing effects when the aircraft in which the platform is mounted carries out a vertical or near-vertical climb or dive. The spin axes of the gyros 78, 80 are arranged parallel to the axis 54 of the platform with their input and precession axes mutually at right angles to each other. The spin axis of the gyro 82 is horizontal and radial with respect to the axis 54. Slave torque motors 68, 70, 72 are controlled by the gyros to stabilize the attitude of the platform 50 in space. If the aircraft in which the platform 50 is mounted flies a very accurate loop path the gimbal turnover of the outer roll gimbal will take place very rapidly in order to preserve the required gimbal attitude relationships, thus causing disturbing torques to affect the platform. The action of the microswitch referred to prevents this by starting the gimbal turnover before the vertical climb attitude is reached. An electrical circuit to effect this is described in the Specification also a means of preventing continued action of the motor 74 by the micro-switch, if the aircraft leaves its loop path in the vertical climb attitude to follow a path along an angle of sideslip.