Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1982-04-23
1984-02-14
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
244 31, F41G 700
Patent
active
044311508
ABSTRACT:
A projectile body has a gyro mounted therein including a rotor and a mechanism for supporting the rotor for rotation about a spin axis initially coincident with the longitudinal axis of the projectile body and pivotable away from the longitudinal axis of the projectile body. The rotor is initially locked to the projectile body so that it is spun with the projectile body during launch. Thereafter, the rotor is unlocked and the projectile body is de-spun to a relatively slow rate of rotation while transferring angular momentum to the free spinning rotor which continues to rotate at a high rate relative to the projectile body. Rotationally phased steering commands, which are generated from on-board homing sensor signals or up-link data signals received from a remote error sensor, are applied to a linear actuator within the projectile body. The actuator pivots the spin axis of the rotor away from the longitudinal axis of the projectile body. The resulting precession torque of the spinning rotor induces a change in the angle of attack between the projectile body axis and the actual velocity vector of the projectile thereby inducing midcourse trajectory shaping.
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General Dynamics Pomona Division
Jester Michael H.
Johnson Edward B.
Jordan Charles T.
Martin Neil F.
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