空间配试目标在轨释放与高精度轨道预报技术

On-Orbit Separation and High-Precision Orbit Prediction for Pointed Targets in Space Test

针对航天装备试验和训练任务需要,采用脉冲推力机动模型近似空间配试目标在轨释放过程,建立高斯型摄动运动方程来定量描述推力产生的瞬时速度增量与轨道要素变化的关系,解决了分离后目标初始轨道确定问题,并利用春分点轨道要素变量消除方程的奇异性。确定在目标运动微分方程中需要考虑的主要摄动因素,给出了每种摄动力加速度模型,综合考虑预报精度和模型复杂度实现目标高精度轨道预报。仿真计算表明目标初始轨道确定相对某航天器仿真软件结果误差不大于1.576%,并且仿真分析了目标轨道衰减特性和目标相对卫星可视距离的变化,对于航天任务中卫星伴飞轨道设计、目标分离窗口选择、目标最佳初始位置确定具有重要参考作用。

In order to determine the initial orbit of the pointed target after separation in space test,the impulse thrust maneuver model is proposed for approximating the target separating process in orbit,and the Gauss perturbation motion equation whose singularity has been eliminated by using the vernal equinox orbital elements,is established to quantitatively describe the relationship between the increment of instantaneous velocity caused by the thrust and the change of orbital elements.Under the main perturbation forces having a marked impact on the dynamic differential equation of the target and the consideration of the obit prediction precision and modeling complexity,the method of high-precision orbit prediction for the target is developed by each selected perturbation acceleration formula.Simulation results show that the relative error of the initial values of the target orbit compared with the data of a certain spacecraft simulation software is not more than 1.576%.The decay characteristics of the target orbit and the variation of the visible distance of the target relative to the satellite are analyzed,which have important value for reference to orbit design of the accompanying satellite,separation window scheme and optimal initial orbit determination for the target in space test.