Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1975-10-15
1977-03-01
Pendegrass, Verlin R.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
74 51, F41G 700
Patent
active
040098486
ABSTRACT:
A gyro seeker which may be employed and housed in the nose section of a cannon launched missile. The gyro seeker functions in a dual mode in that it detects either laser designated targets or targets emitting infrared radiation. Structurally, the gyro seeker comprises a spherically shaped gyro element hydrostatically supported on a gas bearing surface within a spherical cavity of a spherically shaped platform. The gyro in turn supports optical and detector/cryostat assemblies for tracking and detecting desired targets. The platform is similarly hydrostatically supported on gas bearings within the housing. The platform is restrained on the base of the missile by a trapeze mechanism which limits the platform to two-degrees-of-freedom. Means are provided for torquing both the gyro and the platform. Additional means are provided to allow the gyro seeker to withstand the high induced acceleration forces of cannon launching.
REFERENCES:
patent: 2963973 (1960-12-01), Estey
patent: 3756538 (1973-09-01), McLean
patent: 3920200 (1975-11-01), Evans et al.
Albert William Charles
Zoltan Bart Joseph
Kennedy Thomas W.
Pendegrass Verlin R.
The Singer Company
Webb Thomas H.
Wright Laurence A.
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