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
- 2013.10
- 수록면
- 363 - 368 (6page)
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초록· 키워드
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This paper deals with the critical arithmetic analysis of the Attitude Determination System design of Nanosatellites considering the sensor combination model considering finely-selected MEMS based Gyroscopes, Magnetometers and Sun Sensors respectively. Though the competency for achieving higher accuracy for proper positioning of a Nano-satellite is being experimented across the globe effectively, but still there is an absolute need for recognizing the appropriate methodology to enhance their performance withstanding the harsh space environment at different instances. The essential parameters for both the true model and the measurement model are studied and simulated utilizing advanced techniques for obtaining accurate attitude along three axes accordingly. Two distinct attitude determination configurations have been discussed, simulated and compared with significant reasoning being described. One with the combination of Extended Kalman Filter (EKF) and TRIAD algorithm and other with Unscented Kalman Filter (UKF) and TRIAD algorithm. Using these configurations, the critical aspects like power consumption and sensor operation at diverse functioning situations are being conferred. The results show significant variation in accuracy deriving important conclusions on using distinct configuration on board statistically. This research is essentially done to obtained statistical results on unique sensor fusion concept with a different configuration applied which will be practically tested in near future.
목차
Abstract
1. INTRODUCTION
2. EQUATIONS OF SPACECRAFTDYNAMICS
3. SIMULATIONS
4. CONFIGURATION ANALYSIS
5. CONCLUSION
REFERENCES
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