Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1987-01-16
1989-05-16
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
102384, F41G 722
Patent
active
048303119
ABSTRACT:
When a homing head or seeker is mounted on-board a missile, the inertial reference provided by the seeker may be contaminated to some extent by the motion of the missile body. To alleviate this, seekers are sometimes gimballed and use rate or position gyros or they may be momentum-stabilized--the seeker itself providing the inertial reference. However, gyros are both complex and expensive, and momentum-stabilized seekers tend to have large inertias making it difficult to achieve high scan rates. The guidance system described herein allows the establishment of inertial references via information derived from a seeker which need not be isolated from the missile body, the seeker having a range measuring function which, possibly in combination with one or more accelerometers, is used to control pitch, yaw, roll and stabilization of the missile.
REFERENCES:
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Garnell, P. and East, D. J., "Homing Heads and Some Associated Stability Problems", Guided Weapon Control Systems, Pergamon Press, 1980, Chaper 8, pp. 185-197.
Pritchard Alan J.
Stanley John D.
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