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Volume 40 Issue 7
Jul.  2014
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Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(7): 905-909.
Ji Xiaoqin, Xiao Lihong, Chen Wenhuiet al. Optimal multi-impulse rendezvous based on T-H equations[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(7): 905-909. doi: 10.13700/j.bh.1001-5965.2013.0488(in Chinese)
Citation: Ji Xiaoqin, Xiao Lihong, Chen Wenhuiet al. Optimal multi-impulse rendezvous based on T-H equations[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(7): 905-909. doi: 10.13700/j.bh.1001-5965.2013.0488(in Chinese)
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Optimal multi-impulse rendezvous based on T-H equations

doi: 10.13700/j.bh.1001-5965.2013.0488

  • 1. National Key Laboratory of Science and Technology on Aerospace Intelligent Control, Beijing 100854, China;

  • 2. Beijing Aerospace Automatic Control Institute, Beijing 100854, China

  • Received Date: 21 Aug 2013
  • Publish Date: 20 Jul 2014
    Abstract
  • For rendezvous near an elliptic reference orbit, relative motion was described by T-H equations. One time-fixed fuel-optimum multi-impulse rendezvous method was proposed to determine the optimal impulse and its time. If J2 perturbation or the far initial relative distance was considered, the T-H equations linearization error couldn't be ignored, while the trajectory integration was more time-consuming and the optimal convergence rate decreased. For this problem, a new method was put forward that the current node state could be predicted with the orbit element computed by the previous one. It was very simple and valid for making optimal convergence faster. Based on the optimal impulse time, the trajectory numerical integration was carried out to verify the rendezvous precision. The results indicate that the terminal position has higher accuracy up to 75 m even under J2 perturbation and the initial relative distance of 1 000 km.

     

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