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Earth-moon Trajectory Optimization Using Solar Electric Propulsion

机译：利用太阳能推进的月球轨道优化

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摘要

The optimization of the Earth-moon trajectory using solar electric propulsion is presented. A feasible method is proposed to optimize the transfer trajectory starting from a low Earth circular orbit (500 km altitude) to a low lunar circular orbit (200 km altitude). Due to the use of low-thrust solar electric propulsion, the entire transfer trajectory consists of hundreds or even thousands of orbital revolutions around the Earth and the moon. The Earth-orbit ascending (from low Earth orbit to high Earth orbit) and lunar descending (from high lunar orbit to low lunar orbit) trajectories in the presence of J_2 perturbations and shadowing effect are computed by an analytic orbital averaging technique. A direct/indirect method is used to optimize the control steering for the trans-lunar trajectory segment, a segment from a high Earth orbit to a high lunar orbit, with a fixed thrust-coast-thrust engine sequence. For the trans-lunar trajectory segment, the equations of motion are expressed in the inertial coordinates about the Earth and the moon using a set of nonsingular equinoctial elements inclusive of the gravitational forces of the sun, the Earth, and the moon. By way of the analytic orbital averaging technique and the direct/indirect method, the Earth-moon transfer problem is converted to a parameter optimization problem, and the entire transfer trajectory is formulated and optimized in the form of a single nonlinear optimization problem with a small number of variables and constraints. Finally, an example of an Earth-moon transfer trajectory using solar electric propulsion is demonstrated.
机译：提出了利用太阳电推进对月球轨道的优化方法。提出了一种可行的方法来优化从低地球圆形轨道（500 km高度）到低月球圆形轨道（200 km高度）的转移轨迹。由于使用了低推力的太阳能电推进，整个传输轨迹包括围绕地球和月球的数百甚至数千次轨道公转。利用解析轨道平均技术，计算了存在J_2扰动和遮蔽效应的地球轨道上升（从低地球轨道到高地球轨道）和月球下降（从高月轨道到低月轨道）的轨迹。直接/间接方法用于优化跨月球轨迹段（从高地球轨道到高月球轨道的部分）的控制转向，并具有固定的推力-推力-推力发动机顺序。对于跨月运动轨迹段，运动方程式是使用一组非奇异的等分要素（包括太阳，地球和月球的引力）在围绕地球和月球的惯性坐标中表示的。借助解析轨道平均技术和直接/间接方法，将地月转移问题转换为参数优化问题，并以单个非线性优化问题的形式，以较小的形式制定和优化了整个转移轨迹。变量和约束的数量。最后，说明了利用太阳能推进的地月转移轨迹的一个例子。

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