摘要
为减少交会对接过程中轨道面修正的推进剂消耗,考虑到地球交会对接任务中两航天器高度差异带来的升交点漂移速度差异的影响,对追踪航天器发射时刻选取进行了分析,提出了精确发射时刻的迭代计算方法。仿真结果表明该计算方法能够快速精确地得到交会对接任务发射时刻。
The difference of ascending node drift speed caused by difference of orbit height in earth rendezvous is considered to reduce the propellant loss caused by orbit adjustment during rendezvous and docking. The choosing of chaser launch time is analyzed and an iterative method is proposed to calculate the launch time. The simulation results show that the rendezvous and docking launch time can accurately and rapidly acquired by this method.
出处
《载人航天》
CSCD
2010年第4期37-41,45,共6页
Manned Spaceflight
关键词
交会对接
发射时刻
升交点
Rendezvous and Docking
Launch time
Ascending node
