Aerodynamic surface distension system for high angle of attack forebody vortex control
AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorPeter T. Zell
Life of this patent
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Abstract
A deployable system for assisting flight control under certain flight conditions, such as at high angles of attack, whereby two inflatable membranes are located on the forebody portion of an aircraft on opposite sides thereof. The members form control surfaces for effecting lateral control forces if one is inflated and longitudinal control forces if both are inflated.
Claims11
An aerodynamic surface distension system for generating control forces on an aircraft, the system comprising:
- first and second inflatable membranes disposed symmetrically on opposite sides of a forebody portion of the aircraft, each membrane being substantially flush with an outer surface of the forebody portion in a non-deployed position and extending radially outwardly of the forebody outer surface when in a deployed position, and each membrane defining an interior chamber and an exterior surface, the exterior surfaces of the first and second membranes comprising first and second control surfaces when inflated;
- and
- inflatable means for moving the first and second control surfaces from the non-deployed position to the deployed position at high angles of attack.
An aerodynamic surface distension system for generating control forces on an aircraft having a forebody, the system comprising:
- first and second inflatable members disposed on opposite sides of the forebody symmetrically about a vertical plane of the aircraft;
- and
- means for selectively inflating the first and second inflatable members to effect a desired control force at high angles of attack.
Dependencies are inferred from the claim text.