Scalar Adaptive Kalman Filtering for Stellar Inertial Attitude Determination

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This paper describes attitude determination algorithm for the low earth orbit(LEO) spacecraft using stellar inertial sensors. The cascaded gym/star tracker extended Kalman filter is constructed to fuse two sensor data. And then the smoothing of the measurement are proposed for an unreasonable jump of star tracker. The smoothing algorithm for the rejection of star tracker error jumps is designed by scalar adaptive filter. The proposed algorithms operate to process the measurement of gyro/star tracker Kalmari filter, therefore, it is comparatively simple to apply these methods to other integration systems. Simulations to gym/star tracker integrated system show that the proposed method is effective.
Publisher
한국항공우주학회
Issue Date
2002-11
Language
English
Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES , v.3, no.2, pp.88 - 94

ISSN
1229-9626
URI
http://hdl.handle.net/10203/18622
Appears in Collection
AE-Journal Papers(저널논문)
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