一种采用有限推力的航天器轨道机动方法

A Orbit Maneuver Method of the Spacecraft with Finite Thrust

摘要: 以采用有限推力的航天器轨道机动问题为研究对象，根据航天器的运动模型，构建了轨道转移的两点边值问题，给出了发动机开关函数，设计了开关逻辑，应用非线性规划求解两点边值问题，得到了精确的发动机开关时刻和推力方向。最后，用仿真算例验证了本文方法的有效性。

Abstract: Taking the orbit maneuver problem of spacecraft with finite thrust as the research object, the two-point boundary value problem of orbit transfer is constructed according to the motion model of spacecraft. The engine switching function is given and the switching logic is designed. Then, the two-point boundary value problem is solved by nonlinear programming, and the accurate engine switching time and thrust direction are obtained. Finally, a simulation example is given to verify the effectiveness of the proposed method.