Invention Grant
US08418958B2 Landing gear actuation control system 失效
起落架起动控制系统

Landing gear actuation control system
Abstract:
A hydraulic control system for an aircraft landing gear system has a hydraulic pressure source connected to a hydraulic fluid pressure transmission line, and at least one hydraulic actuator for extending and/or retracting a landing gear. A supply valve and a direction valve are arranged in series along the hydraulic fluid pressure transmission line. The supply valve and direction valve are adjustable to control the hydraulic pressure supplied to the at least one hydraulic actuator. The control system also controls uplock actuators.
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