Research on Optimum Evading Strategy from Collision for Spacecraft

摘要：

This paper analyzes the colliding conditions for two orbital objects with different orbital planes.Using secular perturbations of SGP4/SDP4 propagator the time difference the two objects passing the intersection and the corresponding altitude difference can be computed.And after obtaining collision warning information the iteration method of finding optimum velocity increment is given for evading on the basis of orbital adjust.Then considering simplified perturbations the relations between the velocity increment in-track and the passing time difference is discussed which can provide the basic efficiency of the maneuver strategy.

作者: HAN Lei LI Cong-Ying BAI Xian-Zong CHEN Lei

作者单位: Naval Aeronautical and Astronautical University,Yantai 264001,P.R.China College of Aerospace and Material Engineering,National Univ.of Defense Technology,Changsha 410073,P.

会议类型: 国际会议

会议名称: The 30th Chinese Control Conference(第三十届中国控制会议)

会议地点: 烟台

会议语种:英文

页码: 1-5

在线出版日期: 2011-07-01（万方平台首次上网日期，不代表论文的发表时间）