Patent ID: 6491261
Filing Date: 2002-12-10
Classification: B64C,Y02T

Abstract:
An apparatus for imparting yaw moment to an air vehicle in flight, comprising;a deployable spoiler mounted upon an upper aerodynamically continuous wing surface, said spoiler being mounted upon said wing surface by a hinge, said hinge preventing the passage of air between said spoiler and said wing surface upon deployment of said spoiler; a deployable deflector mounted upon a lower aerodynamically continuous wing surface, said deflector being mounted on said lower wing surface for deployment in an opposite manner with respect to said spoiler; said deflector having a size approximately equal to that of said spoiler, said deflector being mounted upon said lower wing surface by a hinge, said hinge preventing the passage of air between said deflector and said lower wing surface upon deployment of said spoiler; and, a deployment mechanism in operative engagement with said spoiler and said deflector for simultaneous deployment thereof, said deployment mechanism being selectively operable to selectively deploy said spoiler and said deflector, said deployment mechanism being a kinematic linkage having a pair of arcuate deployment arms, one of said arcuate deployment arms being attached to said spoiler, and one of said arcuate deployment arms being attached to said deflector, respectively.