摘要
以未来载人火星探测任务为背景,提出了混合推进的轨道方案,即行星中心轨道段采用脉冲推力变轨,行星际航行轨道段采用小推力变轨的策略。建立了日心段三自由度动力学模型,利用"能量等高线"图选取了几组典型脉冲往返轨道作为标称轨道:最小能量轨道、快速转移轨道和短期停留轨道。在此基础上设计了与之对应的行星际航行段小推力最优转移轨道,得到混合推进的轨道方案。最后通过与脉冲轨道的燃料消耗对比,分析了混合推进轨道方案的可行性。研究表明,此类方案较好地结合了脉冲变轨飞行时间短的优势和小推力变轨省燃料、任务灵活的优势。
Taking human exploration of Mars in the future as background, hybrid engines were introduced to trajectory maneuvers, namely the combination of high-thrust engines for planetary flight and low-thrust engines for interplanetary flight. The dynamic model of three degree of freedom was established and the energy requirement was plotted in ＂pork chop＂ figures. The representative roundtrip trajectories were chosen as nominal trajectories： the minimal energy trajectories, the fast transfer trajectories and the ＂short-stay＂ trajectories. The optimal low-thrust interplanetary trajectories were designed based on the nominal trajectories. Finally, the fuel consumption of these trajectory schemes was contrasted with those of pure impulsive trajectory schemes. And the feasibility of combined propulsion trajectory schemes was analyzed. The investigation indicates that these schemes combine the advantages of high-thrust in short flight time and low-thrust in little fuel consumption and high mission flexibility.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2011年第11期2546-2551,共6页
Journal of System Simulation
关键词
载人火星任务
混合推进
转移轨道
燃料消耗
manned Mars mission
combined propulsion
transfer trajectory
fuel consumption
