GB662834A - Improvements in or relating to gyroscopic indicating or steering systems - Google Patents

Abstract

662,834. Electric indicating systems. BENDIX AVIATION CORPORATION. Aug. 23, 1945. [Sept. 21, 1944] No. 21624/45. Class 40 (i). [Also in Groups XX and XXXV] In a system for operating a heading indicator or course-controlling device by integrating the rate of turn of an aircraft, ship, &c. the precession torque of a gyro 10 with its spin axis horizontal and transverse to line of flight, etc. is opposed by the torque of an eddy current coupling device 33, 35 driven by an induction motor 28 which runs when precessional movement of the gyro moves the primary of a transformer 22 in relation to its secondary and so cause an output which is amplified and fed to winding 27 of the motor. The motor also drives a pointer 47 which thus registers the change of heading. During straight flight, the induction motor is controlled by the output signal of a selsyn device 50 responsive to an inductor compass of the static type. In the case of an aircraft, the springs 15, 16 permit the precession of the gyro and the pointer 41 indicates the rate of turn. Springs 15, 16 are omitted when the device is employed in a ship and the rate of turn indication is not given. The system is also described as applied to the control of a rudder, as for example, in the automatic steering system described in Specifications 537,514, [Group XXXV], 559,327 572,213, [Group XX], and 662,833, [Group XXXV], are referred to.