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
- 학술저널
- 저자정보
- 저널정보
- 대한기계학회 Journal of Mechanical Science and Technology Journal of Mechanical Science and Technology Vol.19 No.9
- 발행연도
- 2005.9
- 수록면
- 1,695 - 1,705 (11page)
이용수
초록· 키워드
오류제보하기
Reaction wheels and thrusters are commonly used for the satellite attitude control. Since satellites frequently need fast maneuvers, the minimum time maneuvers have been extensively studied. When the speed of attitude maneuver is restricted due to the wheel torque capacity of low level, the combinational use of wheel and thruster is considered. In this paper, minimum time optimal control performances with reaction wheels and thrusters are studied. We first identify the features of the maneuvers of the satellite with reaction wheels only. It is shown that the time-optimal maneuver for the satellite with four reaction wheels in a pyramid configuration occurs on the fashion of single axis rotation. Pseudo control logic for reaction wheels is successfully adopted for smooth and chattering-free time-optimal maneuvers. Secondly, two different thrusting logics for satellite time-optimal attitude maneuver are compared with each other : constant time-sharing thrusting logic and varying time-sharing thrusting logic. The newly suggested varying time-sharing thrusting logic is found to reduce the maneuvering time dramatically. Finally, the hybrid control with reaction wheels and thrusters are considered. The simulation results show that the simultaneous actuation of reaction wheels and thrusters with varying time-sharing logic reduces the maneuvering time enormously. Spacecraft model is KOrea Multi-Purpose SATellite (KOMPSAT) -2 which is being developed in Korea as an agile maneuvering satellite.
목차
Abstract
1. Introduction
2. Dynamic Characteristics of Attitude Control System
3. Time-Optimal Maneuvering Feature with Pyramid Reaction Wheel System
4. Time-Optimal Maneuvering Feature with Thrusting Logics
5. Time-Optimal Maneuvering Feature with Thrusters And Reaction Wheels in Hybrid Fashion
6. Conclusions
Acknowledgments
References
참고문헌 (15)
참고문헌 신청
Bilimoria, K. D. and Wie, B., 1993, “Time Optimal Three-Axis Reorientation of a Rigid Spacecraft," Journal of Guidance, Control, and Dynamics, Vol.16, No.3, pp.446~452.
Byers, R. M. and Vadali, S. R., 1993, “Quasi-Closed-Form Solution to the Time-Optimal Rigid Spacecraft Reorientation Problem," Journal of Guidance, Control and Dynamics, Vol.16, No.3, pp.453~461.
Hurtado, J. E. and Junkins, J. L., 1998, “Optimal Near-Minimum-Time Control," Journal of Guidance, Control, and Dynamics, Vol.21, No.1, pp.172~174.
KARI and HAU, 2003, "Varying Time Division Pulsing Method and its Controller for Coupled Thrusting Satellite," Patent Pending in Korea.
Lee, B. H., 2004, "Time Optimal Attitude Maneuvers for Agile Spacecraft with Thrusters and Reaction Wheels," Thesis, M.S., Department of Aerospace and Mechanical Engineering, Hankuk Aviation University, Korea.
Byers, R. M. and Vadali, S. R., 1993, “Quasi-Closed-Form Solution to the Time-Optimal Rigid Spacecraft Reorientation Problem," Journal of Guidance, Control and Dynamics, Vol.16, No.3, pp.453~461.
Hurtado, J. E. and Junkins, J. L., 1998, “Optimal Near-Minimum-Time Control," Journal of Guidance, Control, and Dynamics, Vol.21, No.1, pp.172~174.
KARI and HAU, 2003, "Varying Time Division Pulsing Method and its Controller for Coupled Thrusting Satellite," Patent Pending in Korea.
Lee, B. H., 2004, "Time Optimal Attitude Maneuvers for Agile Spacecraft with Thrusters and Reaction Wheels," Thesis, M.S., Department of Aerospace and Mechanical Engineering, Hankuk Aviation University, Korea.
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