Fault tolerant actuation system for flight control actuators

Details Fault tolerant actuation system for flight control actuators Fault tolerant actuation system for flight control actuators

1996-08-07

1998-09-15

Grant, William

Aeronautics and astronautics

Aircraft control

Automatic

244 76A, 244227, 701 3, B64C 1342

Patent

active

058068058

ABSTRACT:
A fault tolerant actuation system (12) for flight control systems is provided. The fault tolerant actuation system (12) includes a plurality of primary flight computers (14a, 14b, and 14c) with corresponding power control units (24a, 24b, and 24c). Each power control unit includes a remote electronic unit (18a, 18b, and 18c), an electro-hydraulic servo valve (26a, 26b, and 26c), and an actuator (28a, 28b, and 28c). The actuators are linked to a flight control surface (30) to control its position. The electro-hydraulic servo valves (26a, 26b, and 26c) and the actuators (28a, 28b, and 28c) include sensors that monitor their operation. Each RE (18a, 18b, and 18c) generates a control current (i.sub.1, i.sub.2, and i.sub.3) based upon commands of the corresponding primary flight computer as well as feedback data transmitted from the sensors of the corresponding electro-hydraulic servo valve and actuator only. The feedback data is transmitted along separate servo loops having separate compensations (66a, 70a). A current equalization control (34a, 34b, and 34c) equalizes the control currents with one another. A force fight equalization control (36a, 36b, and 36c) equalizes the forces of the actuators with one another.

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