摘要
使用混合推进方式设计地-月圆型限制性三体模型下的最省燃料转移轨道。将化学发动机以及电推进发动机的燃料消耗总和作为目标函数进行优化,推导一阶必要条件和雅可比矩阵。选择从近地圆轨道出发到达地-月L1附近Halo轨道的转移轨道为例测试上述方法。仿真结果表明,相比发射脉冲固定的情况,混合推进方式进一步降低了燃料消耗,而且给出了飞行时间和燃料消耗不同的组合方式,给予任务设计更大的灵活性。
Trajectory optimization with hybrid propulsion system is studied under Earth-Moon circular restricted threebody model. The total fuel consumption of both chemical and electrical propulsion systems is minimized, and based on the calculus of variation, the first-order necessary condition and analytic Jacobian are derived. These methods are applied to Earth-Moon L1 minimum-fuel trajectory optimization, the simulation reveals that this kind of methods afford various combination of flight time and total fuel consumption, thus giving a greater flexibility in the mission design.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2015年第8期869-876,共8页
Journal of Astronautics
基金
国家自然科学基金(11102007)
关键词
轨道优化
电推进
最优控制
三体问题
混合推进
Trajectory optimization
Electric propulsion
Optimal control theory
Three-body problem
Hybrid propulsion
