Multi-axis force stick, self-trimmed aircraft flight control sys

Details Multi-axis force stick, self-trimmed aircraft flight control sys Multi-axis force stick, self-trimmed aircraft flight control sys

1982-01-18

1983-12-13

Gruber, Felix D.

Boots, shoes, and leggings

244177, 244223, 364433, 364161, 7386205, G06G 770, B64C 1144

Patent

active

044208081

ABSTRACT:
A four axis force stick provides signals indicative of force applied to the stick in an axis corresponding to a control axis of an aircraft, including pitch, roll, yaw and lift/speed. The force-related signals are applied through proportional and integral gain signal paths to operate electrohydraulic servos that control the aerodynamic surfaces of the aircraft, such as the cyclic and collective blade pitch of the main rotor and the tail rotor blade pitch of a helicopter, or the ailerons, rudder, elevator and thrust of a fixed wing aircraft. Signal conditioning provides a dead band to avoid integrating minute, inadvertent force stick signal outputs, and vernier sensitivity at low forces with high gain at high forces. Analog and digital embodiments are discussed. The relationship between this wholly new mode of aircraft control and ancillary aircraft functions, such as ground steering, autopilot and stability functions, are also discussed.

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patent: 4330829 (1982-05-01), Fischer et al.

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