Adaptive harmonic disturbance compensation system

Aeronautics and astronautics – Spacecraft – Attitude control

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Details

244171, 244172, 244173, 701 13, B64G 126, B64G 136

Patent

active

058068040

ABSTRACT:
A spacecraft (10) carries a solar panel (17) which rotates to follow the sun, and also carries various thrusters (20). Thruster plume impingement on the solar panel affects the torque applied to the spacecraft body (12) in a manner which depends upon solar panel angle. The errors in the thrust during stationkeeping tend to perturb attitude, especially early in the maneuver, because of the delay inherent in the attitude control loop. A torque bias is summed with the residual torque demand signal to correct for the errors in torque. The torque bias signal is generated by a Fourier model of the torques, updated by an adaptive tuning filter, so that successive stationkeeping maneuvers progressively adapt the amplitude and phase of the Fourier coefficients in a manner which tends to minimize the residual torque demand and attitude error. Thus, the torque bias signal automatically approaches the correct value.

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
patent: 5687933 (1997-11-01), Goodzeit et al.

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