Aeronautics and astronautics – Missile stabilization or trajectory control – Stabilized by rotation
Patent
1966-03-15
1995-02-28
Lobo, Ian J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Stabilized by rotation
244 321, F42B 1002, F42B 1060
Patent
active
053930126
ABSTRACT:
A missile comprising a first rotatable portion arranged for rotation relative to a second rotatable portion of the missile, the first rotatable portion being adapted to be subjected to a thrust causing it to rotate in one sense during the flight of the body and in the absense of any restraining or opposing forces, and said second rotatable portion being adapted to be subjected to a thrust causing it to rotate in the opposite sense during the flight of the body, steering means on said first rotatable portion for exerting a thrust thereon away from the axis of rotation thereof to produce a steering effect on the missile or body, a free gyroscope mounted in the first rotatable portion and arranged to generate an electrical signal representative of the roll deviation of the first rotatable portion from a predetermined roll attitude in space and electromagnetic braking means responsive to said electrical signal to brake the first rotatable portion against the second rotatable portion to bring said first rotatable portion to said predetermined roll attitude and to hold it in that attitude.
REFERENCES:
patent: 2850251 (1958-09-01), Joerndt
patent: 3067681 (1962-12-01), Beman
patent: 3111088 (1963-11-01), Fisk
Lobo Ian J.
Shorts Missile Systems Limited
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