Electro/hydraulic system for a 2 door thrust reverser
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United States of America Patent
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Oct 13, 1998
Grant Date -
N/A
app pub date -
Dec 5, 1995
filing date -
Sep 13, 1995
priority date (Note) -
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Abstract
A thrust reverser for a turbo-fan engine having an improved system for security against inflight inadvertent deployment. The reverser has two pivoting doors for use on engines mounted on an aircraft rear fuselage or under the aircraft wing. The pivoting doors are positioned forward of an aft ring structure that is essentially the nacelle exit nozzle in forward thrust mode. The pivoting doors are actuated by a hydraulic actuator and are locked and unlocked by hook locks operated by an electric solenoid on one side of the door and a small hydraulic actuator on the opposite side. The two locking systems are completely independent, thereby assuring that an inadvertent in-flight deployment will not occur as a result from failure, faulty command or maintenance malpractice.
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