太阳帆飞行器轨道动力学分析

Orbit Dynamics Analysis of Solar Spacecraft

通过分析对轨道要素影响最大的加速度分量,使太阳帆总是位于光压力沿这个加速度方向的分量最大的方位。通过分析轨道要素调整时的相互影响关系,提出了同时修正多种轨道偏差的控制方案。对处于地球静止轨道上太阳帆飞行器的轨道调整进行了数值仿真。结果证明利用太阳光压力进行轨道调整是可行的,而且有利的太阳方位是进行快速有效的轨道调整的必要条件。

A sail force control algorithm is proposed, first analyzing the acceleration components to determine which one affects the orbit elements most and then continuously orienting the sail to maximize the solar radiation pressure （SRP） force along the direction of this component. Then through the analysis of the interactional relations of the orbit elements when they are modified, a control strategy is proposed to correct several orbit deviations at the same time. The oblateness perturbation of the Earth J2 term only, as well as the gravitational perturbation of the sun and the moon is considered in the numerical simulation, while atmospheric drag and shadowing effects of the Earth are neglected. Numerical results indicate that using a solar sail to fulfill the task of orbit corrections is feasible. Furthermore, an appropriate orientation of the sun is a necessary condition of quick and efficient orbit modification.