Aeronautics and astronautics – Missile stabilization or trajectory control – Externally mounted stabilizing appendage
Patent
1992-06-04
1994-11-29
Tudor, Harold J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Externally mounted stabilizing appendage
102400, 244 31, 244 321, F42B 1000, F42B 1500
Patent
active
053682556
ABSTRACT:
A missile includes a missile body having a nose, a tail, and a center of gravity therebetween. A plurality of blades are arranged symmetrically around the missile body at a location between the nose and the center of gravity. The blades are deployable from a stowed position folded flat against the body of the missile to a deployed position extending outwardly from the body of the missile, and are mounted so as to be biased toward the deployed position. A retaining wire extends circumferentially around the body of the missile and captures the blades thereunder. The retaining wire may be controllably severed by a pyrotechnic device to release the blades to extend to the deployed position. The extended blades cause the missile to tumble from a first stable orientation to a second stable orientation, permitting it to be quickly pointed in the opposite direction without expenditure of fuel.
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Brown Charles D.
Denson-Low Wanda K.
Heald Randall M.
Hughes Aircraft Company
Tudor Harold J.
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