Finless aerodynamic control system
AssigneeThiokol Corporation
InventorsSteven R. Wassom, Girard H. Rapp, Robert B. Smalley
Life of this patent
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Abstract
A control system for use in missiles and other projectiles which provides pitch, yaw and roll control. The control system includes two opposing pairs of flaps configured in the aft end of the missile case. Each flap is attached for rotation about its leading edge. Prior to actuation, the flaps conform to the exterior surface of the missile. Upon actuation, the flaps extend into the airstream to induce aerodynamic forces. The axis of rotation of each flap is positioned at an oblique angle to the radial plane of the missile.
Claims13
A control system for providing control in a projectile having an elongate case, the control system comprising:
- a first pair of flaps configured in opposing sides of the projectile case, each flap including a leading edge which is attached for rotation about an axis oriented at a first oblique angle to the radial plane of the projectile;
- a second pair of flaps configured in opposing sides of the projectile case, each flap of the second pair including a leading edge which is attached for rotation about an axis oriented at a second oblique angle to the radial plane of the projectile, the second oblique angle being oriented in the opposite direction of the first oblique angle;
- and
- means for rotating the first and second pair of flaps.
A control system for providing control in a projectile having an elongate case with a forward and an aft end, the control system comprising:
- a first pair of flaps oppositely positioned in opposing sides of the projectile case towards the aft end of the projectile, each flap having a leading edge and being attached generally at the leading edge for rotation about an axis oriented at a first oblique angle to the radial plane of the projectile;
- a second pair of flaps oppositely positioned in opposing sides of the projectile case towards the aft end of the projectile and spaced equidistantly from the first pair of flaps, each flap of the second pair of flaps having a leading edge and being attached generally at the leading edge for rotation about an axis oriented at a second oblique angle to the radial plane of the projectile, the second oblique angle being equal and opposite to the first oblique angle;
- and
- means for rotating the first and second pair of flaps.
Dependencies are inferred from the claim text.