Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1975-12-08
1979-05-22
Engle, Samuel W.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
74 51, 74 54, 74 56A, 75 57, F41G 700, G01C 1928, G01C 1912, G01C 1924
Patent
active
041555210
ABSTRACT:
A gyro seeker which is capable of use in a cannon launched missile. The gyro seeker is enclosed in a housing mounted in the nose section of the missile. The platform of the gyro seeker supports an optical assembly, a detector, a gyro assembly, and a cryostat for cooling the detector. Means are provided on the outer gimbal of the platform for withstanding the extreme acceleration induced by cannon launching. The platform is torqueable along two axes by a plurality of pole pieces located around its base. A platform caging device is provided to cage the platform during transport and serves a dual function as a means to furnish spin-up gas to the gyro element and cooling gas to the cryostat.
REFERENCES:
patent: 3187588 (1965-06-01), Parker
patent: 3446082 (1969-05-01), Speen et al.
patent: 3756538 (1973-09-01), McLean
patent: 3824865 (1974-07-01), Evans et al.
patent: 3920200 (1975-11-01), Evans et al.
Evans John L.
Hoffman Jay
Krupick Walter J.
Engle Samuel W.
Kennedy T. W.
The Singer Company
Webb Thomas H.
Wright L. A.
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