Apparatus and method for controlling landing gear

A landing gear system includes landing gear (22), an uplock (26) that is releasably engageable with the landing gear (22), an uplock hydraulic actuator (16) operably connected to the uplock (26), a landing gear hydraulic actuator (14) operatively connected to the landing gear, and a controller (C) o...

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Bibliographische Detailangaben
Hauptverfasser:	BOUCHER FREDERIC, RIBAS CLOVIS S
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COSMONAUTICS DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR FLUID-PRESSURE ACTUATORS FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS HEATING HELICOPTERS HYDRAULICS OR PNEUMATICS IN GENERAL LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A landing gear system includes landing gear (22), an uplock (26) that is releasably engageable with the landing gear (22), an uplock hydraulic actuator (16) operably connected to the uplock (26), a landing gear hydraulic actuator (14) operatively connected to the landing gear, and a controller (C) operatively connected to the uplock hydraulic actuator (16) and the landing gear hydraulic actuator. In response to receipt of a command to deploy the landing gear, the controller (C) actuates the uplock hydraulic actuator (16) and the landing gear hydraulic actuator (14) to the UP condition and then actuates the uplock hydraulic actuator (16) and the landing gear actuator (14) to the DOWN condition. An alternative embodiment incorporates a piloted check valve (42) upstream of the landing gear hydraulic actuator. The piloted check valve (42) delays operation of the landing gear hydraulic actuator (14) until release of the landing gear (22) by the uplock (26).