Optimal, Low-Thrust, Earth-Moon Orbit Transfer
Optimal, Low-Thrust, Earth-Moon Orbit Transfer
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DOI：
10.2514/2.4210
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发表时间：
1998
影响因子：
2.6
通讯作者：
A. L. Herman;B. Conway
中科院分区：
文献类型：
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作者：
A. L. Herman;B. Conway
利用非线性规划的搭配方法，找到了最优的低推力地月轨道转移。初始航天器的地球轨道是任意的；月球的轨道是任意的。月球在它的实际轨道上。飞行器动力学包括在离地阶段月球引力的影响和在到达月球阶段地球引力的影响。总传输时间最小。然而，由于推进系统是连续运行的，即不允许有海岸弧，因此弹道也是推进剂最小化的。一个非常低的初始推力加速度为104.1 g，相当于大约32天的8倍，需要地球和月球都转许多圈。忽略第三体重力，即将问题作为两个耦合的两体问题来解决，对最优轨迹的改变很小，例如，将旅行时间减少几个小时。在初始推力加速度相同的情况下，最优轨迹对发动机c型冲量变化不敏感。
Optimal, low-thrust, Earth ‐moon orbit transfers are found using the method of collocation with nonlinear programming. The initial spacecraft Earth orbit is arbitrary; the e nal lunar orbit is arbitrary. The moon is in its actual orbit. The vehicle dynamics include the effects of the moon’ s gravity during the Earth-departure phase and the effects of the Earth’ s gravity during the lunar-arrival phase. Total transfer time is minimized. However, because the propulsion system operates continuously, i.e., no coast arc is allowed, the trajectory is also propellant minimizing. A very low initial thrust acceleration of 10 i 4 g yields e ight times of approximately 32 days requiring many revolutions of both the Earth and the moon. Ignoring third-body gravity, i.e., solving the problem as two coupled two-body problems, changes the optimal trajectory only slightly, for example, decreasing the travel time by a few hours. The optimal trajectory is also insensitive to change in engine specie c impulse so long as the same initial thrust acceleration magnitude is used.