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
- 2014.10
- 수록면
- 870 - 873 (4page)
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초록· 키워드
오류제보하기
In this paper, robust attitude determination based on the indirect extended Kalman filter is proposed. For the nano-satellite, there are only two vectors of magnetic vector and sun vector for vector measurement without redundant sensors. Accordingly, the three-axis attitude determination using conventional algorithm is impossible when one of the vectors is not available. The proposed attitude determination method uses propagation based on satellite attitude dynamics. The gyro measurements are used for a measurement, and angular rates are estimated by measurements and control inputs. Thus the attitude propagation shows much smaller error than conventional attitude update in the simulation results.
목차
Abstract
1. INTRODUCTION
2. SATELLITE DYNAMICS
3. PROPOSED ALGORITHM
4. SIMULATION RESULTS
5. CONCLUSION
REFERENCES
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