NDLI: Stellar inertial attitude determination for LEO spacecraft

Content Provider	IEEE Xplore Digital Library
Author	Wu, A. Hein, D.H.
Copyright Year	1996
Description	Author affiliation: Hughes Aircraft Co., El Segundo, CA, USA (Wu, A.)
Abstract	This paper describes the normal mode attitude determination algorithm for the low earth orbit (LEO) spacecraft using stellar inertial sensors. Included in the algorithm is a 6-state extended Kalman filter (EKF) which corrects the spacecraft attitude error as well as gyro bias error using celestial observations from star trackers. The detailed derivation of the EKF using a quaternion formulation is given in the paper. Time-domain simulations are presented to show the predicted filter performance which is a function of star density (or number of stars seen), star catalog error, star tracker noise, and gyro noises. Covariance analysis indicates that precision attitude with accuracy better than 12 arc seconds (3 sigma) can be met with the proposed attitude determination and control system hardware components.
Starting Page	3236
Ending Page	3244
File Size	594441
Page Count	9
File Format	PDF
ISBN	0780335902
ISSN	01912216
DOI	10.1109/CDC.1996.573637
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	1996-12-13
Publisher Place	Japan
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Position measurement Low earth orbit satellites Space vehicles Error correction Sensor phenomena and characterization Quaternions Time domain analysis Predictive models Filters Attitude control
Content Type	Text
Resource Type	Article

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