Earth oriented satellite and process for controlling the positio

Aeronautics and astronautics – Spacecraft – Attitude control

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Details

244164, 244170, B64G 132, B64G 124

Patent

active

059574100

ABSTRACT:
A low earth orbiting satellite control arrangement according to the invention has an earth sensor for measuring roll and pitch of the satellite relative to an earth oriented moving reference system, a spin wheel mounted along an axis perpendicular to the orbital plane of the satellite for measuring spin of the satellite, and two magnet coils for generating control. A first of the two magnet coils is aligned substantially in parallel to a roll axis of the satellite, and the second is aligned substantially parallel to the yaw axis. Alternative control algorithms are disclosed for controlling attitude, nutation and spin of the satellite based on information from the earth sensor, spin wheel and an observer which is also mounted on the satellite.

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patent: 5413293 (1995-05-01), Gomberg et al.
patent: 5540405 (1996-07-01), Bender et al.
"Optimal Periodic Control for Spacecraft Pointing and Attitude Determination", Journal of Guidance, Control and Dynamics, 16 (1993) Nov./Dec., No. 6, Washington, D.C.
"Microcomputer Based Adaptive Magnetic Attitude Control of a Spacecraft", 1987 IEEE, CH2461-2/87/0000/0487.
"Magnetic Attitude Control System for Spinning Small Spacecraft", 4th AIAA/USU Meeting, Aug. 27, 1990, Logan 2 (1990).

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