摘要
中止能力是载人登月出现故障时保障航天员安全返回地球的基础。针对混合轨道的中止需求,建立直接中止、多脉冲中止和借助自由返回轨道中止等三种中止方式的轨道计算模型。利用该模型,主要分析了中止轨道在能量需求(用ΔV表征)和返回飞行时间等方面的特性。研究结果表明借助自由返回轨道中止所需能量只相当于最短返回时间直接中止的约1%～5%,但其返回飞行时间在初始段约为最短返回时间的7倍,并随地心距的增加而减小,直至与最短返回时间相当;多脉冲中止在能量需求和返回飞行时间方面均介于两者之间。仿真实例验证了三种中止轨道的有效性。
Abort capability,which is one of the fundamental requirements for manned lunar mission,ensures the astronauts to return safely to the earth when an emergency occurs.Aiming at the abort capability requirement for hybrid trajectory,abort models including direct abort,N-impulse abort and abort using free return trajectory are established.Based on these abort models,the characteristics of abort trajectories such as energy requirement（in terms of ΔV） and return time of flight are mainly analyzed.The results show that the energy requirement of abort using free return trajectory is only equal 1% ～ 5% that of using minimum-time-return direct abort,while its return time of flight is 7 times that of the minimumtime-return abort at the initial stage of the hybrid trajectory,and then decreases as the radius relative to the earth increases,until equals that of the minimum-return-time abort;both of energy requirement and time of flight for N-impulse abort are between those of the two aborts aforementioned.Simulation examples validate the abort models proposed.
出处
《宇航学报》
EI
CSCD
北大核心
2010年第9期2067-2074,共8页
Journal of Astronautics
关键词
载人登月
中止轨道
混合轨道
特性分析
Manned lunar landing mission
Abort trajectory
Hybrid trajectory
Characteristic analysis
