Journal of Mechanical Science and Technology

  • 제20권2호
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  • Pages.177-184
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  • 2006
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  • 1738-494X(pISSN)
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  • 1976-3824(eISSN)
대한기계학회 (The Korean Society of Mechanical Engineers)
권호 표지

An Orbital Design Method for Satellite Formation Flying

  • Cui Hai-Ying (Department of Astronautics & Aeronautics, Tsinghua University) ;
  • Li Jun-Feng (Department of Astronautics & Aeronautics, Tsinghua University) ;
  • Gao Yun-Feng (Department of Astronautics & Aeronautics, Tsinghua University)
  • 발행 : 2006.02.01
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초록

An orbital design method of the formation initialization based on the relative orbital element method is presented. It firstly constructed the relative motion equation of the satellite formation flying in terms of the leader and followers' orbital elements. Then the equation was simplified when the orbit eccentricity of the leader satellite was small. And according to the satellites' mission, a general design method for the relative trajectory was proposed. The advantage of this method is that one can get a very simple analytical formula of each follower satellite's orbital elements when the orbital eccentricity of the leader satellite is zero. The simulation results show that the method is effective.

키워드

참고문헌

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