Actuator system for aircraft control surfaces

Details Actuator system for aircraft control surfaces Actuator system for aircraft control surfaces

1978-09-12

1981-03-17

Frankfort, Charles E.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

74665F, 244 76R, 324207, 340 27R, B64C 1328

Patent

active

042562775

ABSTRACT:
An actuator system for use in symmetrically positioning of control surfaces on opposite sides of an aircraft includes a primary load path for providing power to ball-screw mechanisms for moving the control surfaces between extended and retracted positions. A separate backup shaft is drivingly connected between opposite ends of the primary load path and, in normal service use, is unloaded. In the event of a failure in the primary load path, torque is transmitted through the backup shaft from the unaffected end of the primary load path so as to provide power for actuation of the ball-screw mechanism which otherwise would be affected by the failure in the primary load path. The backup shaft includes a one-piece continuous core whose axis is spaced laterally from the longitudinal axis of the primary load path to increase serviceability, reliability and reduce the likelihood of simultaneous damage to both the backup shaft and the primary load path. Additionally, sensors are provided at opposite ends of the backup shaft for detecting torsional deflection of the shaft as a result of torque being applied to the shaft when there is a failure in the primary system. When torsional deflection in excess of a predetermined amount is detected, a signal indicating such is provided and the signal is a reliable indication of failure in the primary load path inasmuch as substantial torsional deflection can occur only when the backup shaft is loaded as a result of failure in the primary load path.

REFERENCES:
patent: 3317829 (1967-05-01), Kuhrt et al.
patent: 3935754 (1976-02-01), Comollo
patent: 3986689 (1976-10-01), Maltby
patent: 4040272 (1977-08-01), Boyd

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