Attitude control system

Aeronautics and astronautics – Spacecraft – Attitude control

Patent

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Details

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.

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