Hydraulic actuating arrangement for aircraft control surfaces

Aeronautics and astronautics – Aircraft control – Automatic

Patent

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Details

91363A, 244194, 244 83E, 318565, B64C 1340

Patent

active

039557839

ABSTRACT:
A hydraulic actuating arrangement for an aircraft control surface has a control circuit, responsive to a position selection input signal, for providing six nominally identical output control signals. Six pilot valves respectively responsive to the control signals provide six servo pressure signals to respective ones of six intermediate actuators. The intermediate actuators are resiliently coupled to each of two main hydraulic control valves. Three of the intermediate actuators and one of the main control valves are supplied from a first hydraulic pressure source, the remaining three intermediate actuators and the remaining main control valve being supplied from a second hydraulic pressure source. An output actuator is responsive to output pressures from either of the main control valves.

REFERENCES:
patent: 3120787 (1964-02-01), Schmitt
patent: 3136504 (1964-06-01), Carr
patent: 3198082 (1965-08-01), Kerris
patent: 3433125 (1969-03-01), Gemmell
patent: 3496836 (1970-02-01), Jenney
patent: 3679156 (1972-07-01), Redmond, Jr.
patent: 3813990 (1974-06-01), Coppula et al.

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