Nacelle for an aircraft turbojet engine provided with a hydraulic roto-linear actuator of a thrust reverser and of a variable-section nozzle
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United States of America Patent
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Jan 29, 2019
Grant Date -
Oct 18, 2018
app pub date -
Jun 18, 2018
filing date -
Dec 17, 2015
priority date (Note) -
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status (Latency Note)
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Abstract
The present disclosure concerns a nacelle for an aircraft turbojet engine that includes a thrust reverser having a cowl displaceable between a deployed position and a stowed position, a fixed structure, and a secondary nozzle. The nozzle includes panels movable in rotation, and hydraulic actuators for sequenced actuation of the cowl and panels. The actuators include a body mounted on the fixed structure, and a rod mounted in the body and is linked to the cowl and panels via a device for transmitting movement of the actuator to the panel. An actuation system having a hydraulic control device controls the displacement of the rod of the actuator. The actuator further includes a device for alternately displacing the rod in translation relative to the body to cause translation of the cowl, or in rotation relative to the body to cause rotation of the nozzle panel.
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