Patent ID: 9567867
Date: 2017-02-14
CPC Classifications: F01D,F02K

Claim:
1. An aircraft control structure comprising: an engine nacelle comprising a downstream end, the engine nacelle comprising a nozzle structure defining a flow path and configured to exhaust a swirling fluid stream at a nozzle exit, the nozzle structure having an inner surface; a plurality of swirl vanes coupled to the nozzle structure, each having a generally airfoil shape, the plurality of swirl vanes movable relative to the nozzle structure between a deployed state and a non-deployed state, the plurality of swirl vanes cerate with a portion of the nozzle structure to define an outer surface of the nozzle structure in the non-deployed state; and an actuation subsystem configured to cause the plurality of swirl vanes to move from the deployed state to the non-deployed state; wherein, in the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure; wherein, in the deployed state, the plurality of swirl vanes extend radially substantially across the flow path, produce the swirling fluid stream and define a plurality of cut-outs through the nozzle structure; and wherein the plurality of swirl vanes are deployed to assist in drag management of the aircraft and an exit area of the nozzle exit is greater in the deployed state than in the non-deployed state.