Research on Transfer Orbit Based on Electric Propulsion Satellite to Halo Orbit
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摘要: 利用电推进及轨道力学的特性实现节能优化，将限制性三体问题中的稳定不变流形与小推力轨道优化相结合，研究全电推进卫星从地球停泊轨道飞向日地拉格朗日L2点Halo轨道的低消耗转移轨道.航天器的转移轨道分为逃逸段、拼接段与无动力滑行段.在逃逸段卫星沿速度方向加速脱离地球引力，拼接段采用Radau伪谱法进行优化，使航天器以最短时间到达目标Halo轨道的稳定不变流形上，随后航天器电推进系统关机，沿稳定不变流形无动力滑行至目标轨道.基于雅克比积分常数给出拼接段轨道初始猜测值，以先提高切向方向航天器能量避免了全程优化离散点过多难以求解的问题.仿真结果表明，该方法收敛速度较快，对平动点工程任务的初期轨道特性计算具有实际意义.Abstract: Energy-saving optimization was achieved by using the characteristics of low-thrust electric propulsion and the orbital dynamics. The transfer orbit of the spacecraft from the Earth parking orbit to the Sun-Earth L2 point Halo orbit has been studied by combining the invariant manifold in the restrictive three-body problem with the low thrust trajectory optimization. Firstly, the transfer orbit is divided into burn and coast phases. Tangential acceleration was used to decrease Jacobi integration constant rapidly, and then Radau pseudo spectral method was adopted in the burn phases to optimize the orbit so that the spacecraft could reach the stable invariant manifold of the target orbit. When the spacecraft reached stable invariant manifold, it could coast to target halo orbit. The initial transfer orbit was guessed by Jacobi integration constant. Finally, a simulation example of transfer orbit was given to verify the effectiveness of the method. The results show that it is of guiding significance to practical engineering application.
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Key words:
- Low-thrust /
- Invariant manifold /
- Halo orbit /
- Pseudo spectral method
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