固定时间轨道拦截的制导方法研究

Guidance for time-fixed orbital interception

针对摄动影响下的固定时间轨道拦截问题,提出了一种基于虚拟拦截点的导引算法。通过对虚拟拦截点的修正,将摄动下的轨道拦截问题转化为二体假设下的Lambert轨道拦截问题进行求解,使摄动下的拦截问题得到简化。该方法计算过程简单,便于编程实现。仿真结果表明该方法合理有效,并能达到较高的精度。

A guidance law with virtual interception point was presented for the fixed-time orbital intercep-tion problem under the effect of perturbation. By introducing a virtual target interception point, it wasconvenient to make a fixed-time orbital interception in space environment into a quite simple Lambertproblem which is based on the two-body theory. Construction of this algorithm is rather simple and it＇squite convenient to compile a CODEC. Simulation results show that the algorithm is efficient and achievea high precision.