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Characteristic analysis and design of near moon abort trajectory for manned lunar landing mission

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Abstract

The safety of astronauts would be severely threatened if the lunar-landing spacecraft were under an emergency during the near moon phase of flight, which was far from the Earth. For the problem of mission abort caused by the main engine (service propulsion system, SPS) failure during lunar orbit insertion, firstly, the family of trajectories resulted from SPS premature shutdown and corresponding abort trajectories were analyzed; then an algorithm that can be applied to the near moon abort trajectories was proposed using patched-conic technique. The characteristics of the abort trajectory, such as energy consumption and return time of flight, were analyzed and presented. Finally, simulation examples were given to demonstrate various cases of near moon SPS failure. The results of the simulation have validated the approach proposed.

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Authors and Affiliations

  1. College of Mechatronics Engineering and Automation, National University of Defense Technology, Changsha, 410073, China

    WenDe Huang & Wei Wang

  2. College of Aerospace and Material Engineering, National University of Defense Technology, Changsha, 410073, China

    XiaoNing Xi

  3. School of Surveying and Spatial Information System, University of New South Wales, Sydney, NSW, 2052, Australia

    Wei Wang

Authors
  1. WenDe Huang
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  2. XiaoNing Xi
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  3. Wei Wang
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Correspondence to WenDe Huang.

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Huang, W., Xi, X. & Wang, W. Characteristic analysis and design of near moon abort trajectory for manned lunar landing mission. Sci. China Technol. Sci. 53, 3129–3137 (2010). https://doi.org/10.1007/s11431-010-4118-x

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  • DOI: https://doi.org/10.1007/s11431-010-4118-x

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