지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2011.10
- 수록면
- 1,891 - 1,896 (6page)
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초록· 키워드
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In this study an unscented Kalman filter (UKF) based magnetometer and gyro bias estimation algorithm is presented as a part of the attitude determination procedure for a small satellite, which has three magnetometers and three gyros as measurement sensors. Differently from the existing studies both magnetometer and gyro biases are estimated as well as the attitude parameters. Kinematics of the satellite is modeled via using quaternion parameterization. In order to enable estimation of all parameters simultaneously without a high computational cost, two methods known in advance are used. First, quaternion based modeling constraint that is met because of the unit norm of quaternion is overrun by enforcing constraint as a dummy measurement through the measurement model, instead of employing three-element error quaternion state as attitude representation. Second, in filter formulations gyro-based model is used for attitude propagation. Validity of the proposed method is confirmed by simulations.
목차
Abstract
1. INTRODUCTION
2. KINEMATICS MODEL OF THESATELLITE
3. MEASUREMENT SENSOR MODELS
4. UKF BASED ATTITUDEDETERMINATION AND BIAS ESTIMATION
5. SIMULATIONS
6. CONCLUSIONS
REFERENCES
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UCI(KEPA) : I410-ECN-0101-2014-569-000915952