Thrust reverser control mechanism
AssigneeROLLS-ROYCE plc
InventorArnold C. Newton
Life of this patent
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Abstract
A control mechanism for the thrust reverser of an aircraft comprises an open ended conduit, the open end of which operationally protrudes into the airflow over the surface of the aircraft. The airflow over the aircraft creates a partial vacuum within the conduit. A piston is translatable within a cylinder in accordance with the magnitude of the partial vacuum. The position of the piston within the cylinder determines whether the thrust reverser can or cannot be actuated, thereby preventing inadvertent in-flight thrust reverser actuation.
Claims4
A control mechanism for the thrust reverser of an aircraft mounted gas turbine engine comprising means responsive to the air flow over the aircraft as a measure of the forward motion of the aircraft which incorporates said engine and providing an output signal in accordance with the magnitude of said forward motion, and means responsive to said output signal to prevent the operation of said thrust reverser when the forward air speed of said aircraft is within a predetermined range of values.
Dependencies are inferred from the claim text.