Method and apparatus for compensating for solar torque transient

Details Method and apparatus for compensating for solar torque transient Method and apparatus for compensating for solar torque transient

1991-11-27

1994-08-16

Huppert, Michael S.

Aeronautics and astronautics

Spacecraft

Attitude control

244165, 364434, B64G 124

Patent

active

053379810

ABSTRACT:
This invention discloses a method for determining when an orbiting satellite (10) is eclipsed from the sun in order to remove control torques to the satellite (10) which compensate for the disturbance of solar pressure on the satellite (10). A current measuring device (46) measures the current traveling through a particular circuit associated with the satellite (10) which is indicative of the satellite batteries being discharged, as would occur during an eclipse. The measured current is applied to a threshold logic circuit (48) which sends a signal to a control compensator (36) if the measured current exceeds a predetermined threshold level. Consequently, the compensation provided by the control compensator (36) removes the compensation for compensating for solar pressure when the satellite (10) is in an eclipse. In a second implementation, the threshold logic circuit (48) is replaced with a proportionality logic circuit to compensate for the effects of partial eclipses.

REFERENCES:
patent: Re29177 (1977-04-01), Michaelis
patent: 4071211 (1978-01-01), Muhlfelder et al.
patent: 4188666 (1980-02-01), Legrand et al.
patent: 4837699 (1989-06-01), Smay et al.
patent: 4960250 (1990-10-01), Schmidt

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