Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1983-05-31
1985-06-11
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
74 56R, F41G 736, G01C 1928
Patent
active
045223556
ABSTRACT:
An apparatus comprising, inter alia, gyroscope feedback circuitry which aw scanning the rotor magnet of a gyroscope disposed in an associated guided missile system so as to increase the seeker field thereof is disclosed. A signal from the cage coil of the gyroscope having an amplitude approximating a sine function of the angular position of the spin axis of the rotor magnet portion of the gyroscope with respect to the body axis of the associated guided missile is used to generate a constant amplitude drive signal for driving the precession coil of the gyroscope. Scanning, so as to drive the rotor magnet in a predetermined scan pattern is accomplished by phase shifting the signal from the cage coil as a function of its amplitude and then driving the precession coil with the aforementioned constant amplitude drive signal which is phased-locked to the phase shifted or processed cage coil signal.
REFERENCES:
patent: 3351303 (1967-11-01), Depew, Jr. et al.
patent: 3951358 (1976-04-01), De Lano et al.
patent: 4093154 (1978-06-01), McLean
patent: 4264907 (1981-04-01), Durand, Jr. et al.
patent: 4277039 (1981-07-01), Blanning et al.
Beers Robert F.
Jordan Charles T.
The United States of America as represented by the Secretary of
Walden Kenneth E.
Wynn John G.
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