Landing gear actuation control system
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United States of America Patent
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Apr 16, 2013
Grant Date -
Oct 21, 2010
app pub date -
Mar 23, 2010
filing date -
Apr 15, 2009
priority date (Note) -
Expired
status (Latency Note)
Importance
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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