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

作　　者：HUANG WenDe XI XiaoNing WANG Wei 

机构地区：[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

出　　处：《Science China(Technological Sciences)》2010年第11期3129-3137,共9页中国科学(技术科学英文版)

摘　　要：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.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 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]