LOW OBSERVABLE ENGINE AIR INLET SYSTEM

Abstract

A turbine engine inlet system includes a duct 14 to deliver air to the engine, inlet lips 16 and 52 to smooth the entry of air flowing into the duct, a screen 50 between the lips 52 and 16 for passage of inlet air, a forward inlet section 18 submerged within the aircraft skin contour to provide a degree of ram recovery to the duct, and a movable air deflector 20 which is positionable in a retracted position during normal flight, is extendable outward to a second position substantially flush with the screen 50 for maximum protection against foreign object damage (FOD), and is further extendable outward to a third position beyond the screen to provide an air bypass path when the screen is iced-over.

Source: Google Patents

35 USC §181 Secrecy Order

Inventor

• 1DAVID R. SMITH

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