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Review on abort trajectory for manned lunar landing mission

Science china(Technological Sciences) 2010年第10期53卷 2691-2698页

作者： xi xiaoning1, huang wende2 & wang wei2,3.1 college of mechatronics engineering and automation, national university of defense technology, changsha 410073. china 2 college of Aerospace and Material engineering, national university of defense technology, changsha 410073. china 3 School of Surveying and Spatial Information System, university of New South Wales, Sydney, NSW 2052, Australia college of mechatronics engineering and automation National University of Defense Technology Changsha China college of Aerospace and Material engineering National University of Defense Technology Changsha China School of Surveying and Spatial Information System University of New South Wales Sydney Australia

Abort trajectory is a passage that ensures the astronauts to return safely to the earth when an emergency occurs. Firstly,the essential elements of mission abort are analyzed entirely based on summarizing the existing studies. Then,abort trajectory requirement and rational selection for different flight phases of typical manned lunar mission are discussed specifically. Considering a trade-off between the two primary constrains of an abort,the return time of flight and energy requirement,a general optimizing method for mission abort is proposed. Finally,some suggestions are given for china’s future manned lunar landing mission.

关键词： manned lunar landing mission abort trajectory design free return trajectory

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

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Science china(Technological Sciences) 2010年第11期53卷 3129-3137页

作者： huang wende xi xiaoning wang wei college of mechatronics engineering and automation National University of Defense TechnologyChangsha 410073China college of Aerospace and Material engineering National University of Defense TechnologyChangsha 410073China School of Surveying and Spatial Information System University of New South WalesSydneyNSW 2052Australia

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.

关键词： manned lunar landing mission abort trajectory near moon phase characteristic analysis patched-conic technique

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