Attitude control for spacecraft with movable appendages such as

Details Attitude control for spacecraft with movable appendages such as Attitude control for spacecraft with movable appendages such as

1995-10-16

1997-11-18

Grant, William

Aeronautics and astronautics

Spacecraft

Attitude control

244171, 244172, 244173, B64G 126, B64G 136

Patent

active

056879334

ABSTRACT:
A spacecraft includes a three-axis attitude control system. When velocity change thrusters are fired, their plumes impinge on a solar array, at angles which vary with the solar array position. This causes disturbance torques which vary with the solar array position. Disturbance torque information signals or torque bias signals which depend upon the solar array angle are summed with the torque demand signals which control the attitude control system during firing of the velocity change thrusters, to modify the attitude correction torques. The bias torque signals are generated by a Fourier processor based upon stored Fourier coefficients together with signals from a solar array angular position sensor.

REFERENCES:
patent: 4407469 (1983-10-01), Fox
patent: 4537375 (1985-08-01), Chan
patent: 4591117 (1986-05-01), Scott
patent: 4684084 (1987-08-01), Fuldner et al.
patent: 5098041 (1992-03-01), Uetrecht

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