Solar torque estimation for momentum bias spacecraft1
- 64 Downloads
This paper introduces a solar torque estimation algorithm for momentum bias satellites, ultimately benefiting yaw pointing performance and momentum management. A subspace of the solar torque is demonstrated to be unobservable without the use of a rate sensor. By decomposing the solar torque environment into observable and unobservable components, this algorithm may be implemented with or without a rate-sensing gyro. Flight data are presented, sharing recent flight experiences with the algorithm in this paper. This telemetry is derived from several recent, large geosynchronous orbit (GEO) satellites, including one with a 12-meter deployable antenna.
KeywordsTorque Rate Sensor Pitch Axis Earth Sensor Gyro Drift
Unable to display preview. Download preview PDF.
- RODDEN, J. J., MCGOVERN, L. K., HIGHAM, J., and PRICE, X. “Momentum Bias for Spacecraft Attitude Control,” presented as paper AAS 02-003 at the 2002 AAS Guidance and Control Conference, Feb. 6–10, 2002.Google Scholar
- MCGOVERN, L. K. and PRICE, X. “Satellite Harmonic Torque Estimator,” United States Patent 6,672,544, January 6, 2004.Google Scholar
- MCGOVERN, L. K., HIRSCHBERG, P., and PRICE, X. “Solar Torque Estimation for Momentum Bias Spacecraft with Large Deployable Appendages,” presented as paper AAS 06-004 at the 2006 AAS Guidance and Control Conference, Feb. 4–8, 2006.Google Scholar
- SIDI, M. J. Spacecraft Dynamics and Control, Cambridge University Press, Cambridge, England, 1997.Google Scholar
- AGRAWAL, B. N. Design of Geosynchronous Spacecraft, Prentice-Hall, Englewood Cliffs, NJ, 1986.Google Scholar
- GELB, A. (editor) Applied Optimal Estimation, MIT Press, Cambridge, MA, 1974.Google Scholar