PSEUDO CONTROL STICK STEERING SYSTEM FOR AIRCRAFT HAVING A DAMPER SYSTEM

1,171,058. Electric control systems. SPERRY RAND CORP. April 29, 1968 [May 19, 1967], No.20122/68. Heading G1N. Movement of the control stick 1 of an aircraft 8 to produce a change in pitch is sensed by a displacement sensor 20 and force sensor 21, and the difference between the two signals is derived at 23 to augment the control of the elevator 7 via actuator 6, whereby the displacement signal predominates at low speeds and the force signal at high speeds. A pitch damping signal is obtained from a pitch rate gyro 14 and fed through a lag compensation circuit 18 to a summing amplifier 15 to oppose the difference between the displacement and force signals from the control stick 1. Steady pitch change signals are removed by series capacitors 17, 24. The resultant elevator control signals produce desired stability characteristics over a wide range of flight conditions.