| 摘要 |
An aircraft pitch control system which includes a movable tail composed of a powered stabilizer which is angularly movable about a first axis, and elevators mounted on the rear end of the stabilizer which are angularly rotatable about a second axis displaced from the first axis. The stabilizer is controlled by an electric, pneumatic or hydraulically powered actuator, and the elevators are controlled manually through appropriate cables or mechanical linkage. The stabilizer actuator is controlled by movements of the elevators through an appropriate servo mechanism, so that angular movement of the stabilizer follows angular movement of the elevators. In the event of failure of the stabilizer actuator, the stabilizer is locked in a selected position by an automatic lock, and the pitch of the aircraft is controlled manually by the elevators alone.
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