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Three-axis attitude determination via Kalman filtering of magnetometer dataA three-axis Magnetometer/Kalman Filter attitude determination system for a spacecraft in low-altitude Earth orbit is developed, analyzed, and simulation tested. The motivation for developing this system is to achieve light weight and low cost for an attitude determination system. The extended Kalman filter estimates the attitude, attitude rates, and constant disturbance torques. Accuracy near that of the International Geomagnetic Reference Field model is achieved. Covariance computation and simulation testing demonstrate the filter's accuracy. One test case, a gravity-gradient stabilized spacecraft with a pitch momentum wheel and a magnetically-anchored damper, is a real satellite on which this attitude determination system will be used. The application to a nadir pointing satellite and the estimation of disturbance torques represent the significant extensions contributed by this paper. Beyond its usefulness purely for attitude determination, this system could be used as part of a low-cost three-axis attitude stabilization system.
Document ID
19890006580
Document Type
Conference Paper
Authors
Martel, Francois (Ithaco, Inc., Ithaca NY., United States)
Pal, Parimal K. (Ithaco, Inc., Ithaca NY., United States)
Psiaki, Mark L. (Cornell Univ. Ithaca, NY., United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1988
Publication Information
Publication: NASA, Goddard Space Flight Center, Flight Mechanics(Estimation Theory Symposium 1988
Subject Category
ASTRODYNAMICS
Funding Number(s)
CONTRACT_GRANT: N00014-87-C-2092
CONTRACT_GRANT: SC00150
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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