Aeronautics and astronautics – Spacecraft – Attitude control
Patent
1974-10-02
1976-10-05
Blix, Trygve M.
Aeronautics and astronautics
Spacecraft
Attitude control
244 321, 244171, B64G 120
Patent
active
039840727
ABSTRACT:
An attitude control system for a space vehicle in which angular rate signals are generated by rate gyros mounted closely adjacent to gimbaled engines at the rear of a vehicle, and wherein error signals representative of a commanded change in vehicle angle or attitude are obtained from a precision inertial platform located in the nose region of the vehicle. The rate gyro derived signals dominate at high frequencies where dynamic effects become significant, and platform signals dominate at low frequencies where precision signals are required for a steady vehicle attitude. The blended signals are applied in a conventional manner to control the gimbaling of vehicle engines about control axes.
REFERENCES:
patent: 3132828 (1964-05-01), Edinger et al.
patent: 3301508 (1967-01-01), Yamron
patent: 3395874 (1968-08-01), Bartoli et al.
Rupp Charles C.
von Pragenau George L.
Blix Trygve M.
Kelmachter Barry L.
Manning John R.
Porter G. J.
The United States of America as represented by the Administrator
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