Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1979-04-27
1981-07-07
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
F42B 1502
Patent
active
042770386
ABSTRACT:
In a missile system, a simple way to guide a missile in a predetermined tectory from launch to the impacting with a target for optimum warhead penetration of armor by a guided missile. Initially, the missile is guided in yaw by proportional navigation. Subsequently it is guided in pitch first by a pitch programmer until the missile reaches a predetermined gimbal angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a pseudo-time-optimal closed loop controller to direct the missile pitch attitude at a predetermined rate toward a target until said missile reaches another predetermined gimbal angle, and finally by proportional navigation in pitch of the missile to the target.
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Albanes Wilfredo V.
Alongi Robert E.
Bishop Charles M.
Leonard John P.
Yates Robert E.
Bush Freddie M.
Edelberg Nathan
Gibson Robert P.
Jordan Charles T.
The United States of America as represented by the Secretary of
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