Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1976-01-07
1977-07-19
Bentley, Stephen C.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
74 51, 74 54, 74 56A, 74 57, F41G 700, G01C 1928, G01C 1912, G01C 1924
Patent
active
040364534
ABSTRACT:
A torquer system for a gyro device that has a spherically shaped rotor divided into upper and lower hemispheres. The rotor of the gyro is mounted on a gas bearing over a spherically shaped stator and supports an optical assembly positioned parallel to the spin axis of the gyro. The torquer is positioned on the base of the gyro beneath the lower hemisphere of the rotor so as to permit the maximum angular freedom of the rotor and optical assembly. The torquer comprises four pole pieces separated 90.degree. from each other. Each torquer has two pole faces and coils located between pole faces. The coils contain separate windings for bias and control of the torquer. A current flow through the windings of the torquers causes magnetic flux lines emanating from the pole faces to pass through magnetically permeable material affixed to the lower hemisphere of the gyro rotor closing the magnetic circuit. The rotor will be attracted towards the pole face and the magnitude of the force of attraction is indicative of the current passing through the torquer windings.
REFERENCES:
patent: 2527245 (1950-10-01), Cunningham et al.
patent: 2600476 (1952-06-01), Bursack
patent: 3260122 (1966-07-01), Rocks
patent: 3824865 (1974-07-01), Evans et al.
patent: 3920200 (1975-11-01), Evans et al.
Evans John Lorenz
Zoltan Bart Joseph
Bentley Stephen C.
Kennedy Thomas W.
The Singer Company
Webb Thomas H.
Wright Laurence A.
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