Halo轨道间转移的显式制导方法研究

将显式制导方法应用于地月系统L1平动点Halo轨道间的转移问题,用以克服动力学建模误差.通过等时间间隔计算到达目标点的需要速度,得到当前速度与需要速度的矢量差,称为速度增益,其模即为控制冲量.需要速度通过应用Sukhanov-Prado方法求解三体Lambert问题获得.采用圆限制性三体模型(CR3BP)设计标称轨道和进行制导计算,双圆模型(BCM)作为考虑太阳引力的摄动模型进行仿真.结果表明,所提出的方法针对模型误差简单有效、计算速度较快并且所需能耗小.

An Explicit Guidance Strategy in Halo-to-Halo Transfers

An explicit guidance strategy is developed in order to compensate for the perturbations in a real model or a simulation model. The main idea is to add control at equally spaced time points according to the calculation of the required velocity,which is the key point of the method. The required velocity is computed by solving a three-body Lambert problem （3BLP）. The presented method is applied to the Earth-Moon L1 Halo-to-Halo transfer problem where the nominal orbit is obtained from CR3BP,and the simulation is performed taking the bicircular model （BCM） as perturbation model including the solar gravity. It can be easily extended to other systems and transfer types,as well as various dynamics models. Results show that the approach can successfully maintain control of the vehicle and a small amount of propellant are required.