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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。
Based on the future mission of manned Mars exploration, a hybrid orbit propulsion scheme is proposed, that is, the impulse thrust orbit is used in the orbital segment of the planet and the trajectory of small thrust orbit is changed in the interplanetary orbit. The three-degree-of-freedom kinetic model of the heliocentric segment was established and several typical pulse reciprocating orbits were chosen as the nominal orbit: the minimum energy trajectory, the fast transition trajectory and the short-term trajectory by using the “contour map of energy”. On this basis, we design the corresponding small thrust optimal transfer orbit of the interplanetary navigation segment, and get the hybrid propulsion scheme. Finally, by comparing with the fuel consumption of the pulse orbit, the feasibility of the hybrid propulsion scheme is analyzed. The research shows that this kind of scheme better combines the advantage of short flight time of pulse orbit change and fuel saving with small thrust orbit change, with flexible tasks.