Patent 5398887 Issued on March 21, 1995. Estimated Expiration Date: October 12, 2013. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
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.
Other References
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Kolcum, "Delta Clipper Partners Set Goal For Single-Stage-to-Orbit Vehicle", Aviation Week & Space Technology, pp. 55-56, Feb. 3, 1992
Smith, "DC-X Vehicle Nears Flight Test", Aviation Week & Space Technology, pp. 27-28, Mar. 29, 1993
Dornheim, "DC-X Proving Initial Operational Concepts", Aviation Week & Space Technology, pp. 46 & 49, Oct. 11, 1993
Wassom et al., "Integrated Aerofin/Thrust Vector Control for Tactical Missiles", Journal of Propulsion and Power, vol. 7, No. 3, pp. 374-381, May-Jun. 1991
Eggers, Jr. et al., "Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight", National Advisory Committee for Aeronautics, Jan. 18, 195
October 12, 2013. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
