Aeronautics and astronautics – Aircraft control
Patent
1995-01-03
1996-10-15
Culbreth, Eric D.
Aeronautics and astronautics
Aircraft control
244 46, 244 327, B64C 500
Patent
active
055646522
ABSTRACT:
A body spoiler rotatably mounted within a recess formed within opposite sides of the forebody of a supersonic air vehicle and configured to conform with the fuselage of the vehicle. A sensor positioned close to the inlet of each engine powering the flight of the vehicle measures the pressure of the fluid entering the engine. If an engine on one side of the vehicle malfunctions, the pressure sensor sends a deploy signal to the body spoiler mounted on the same side of the vehicle. An actuator receives the deploy signal and rotates the spoiler through an angle which is dependent upon the speed of the vehicle. When deployed, the spoiler generates a shock wave which in turn produces pressure along the forebody thereby creating a yaw moment to substantially counterbalance the yaw moment generated by the malfunctioning engine. A plurality of spoilers can also be pivotably mounted along and about the periphery of the fuselage and used as an emergency aid in generating other forces and moments along and about the three main axes of the vehicle. In addition to providing yaw moment control, spoilers deployed on the crown or keel of the vehicle at supersonic speeds could be used in dive recovery by generating drag and a nose up pitching moment.
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W. T. Kehrer, Design Evolution Of The Boeing 2707-300 Supersonic Transport, Part II, Design Impact of Handling Qualities Criteria, Flight Control System Concepts, and Aeroelastic Effects on Stability and Control pp. 10-1 through 10-10.
Richard E. Boalbey et al., High-Angle-Of-Attack Stability And Control Concepts For Supercruise Fighters pp. 759-784.
Anderson W. C.
Culbreth Eric D.
Donahue B. A.
Ellis Christopher
Gullette R. L.
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