Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1964-09-04
1995-08-08
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
244 327, F42B 1014, F42B 1501
Patent
active
054391881
ABSTRACT:
An air vehicle control system utilizing variable incidence aerodynamic control surfaces deployed from within the missile body and locked in place. Only two control surfaces (instead of the four usually required for a missile which maneuvers in three dimensions) are required. The number of control surfaces required is reduced by utilizing missile roll to achieve control in any direction. Flight control of the air vehicle is achieved by a single pair of aerodynamic control surfaces located forward of the missile center of gravity. In order to produce a turning moment in any direction, the missile is rolled at a predetermined number of revolutions per second. The control surfaces are operated during the proper portion of each missile revolution to achieve the desired directional control.
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Besserer; Missile Engineering Handbook, Van Nostrand Co.; 1958 p. 523.
Locke; Guidance, Van Nostrand Co.; 1955 pp. 286 & 287.
Depew, Jr. Herbert D.
Ernst, Jr. Robert J.
Brown Charles D.
Denson-Low Wanda K.
Heald Randall M.
Hughes Missile Systems Company
Jordan Charles T.
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