miniSAR卫星精密参考轨道设计

为满足轻小型合成孔径雷达(miniSAR)卫星干涉测量任务对空间基线的要求，通过分析卫星参考轨道特性，建立了一套精密参考轨道设计算法。所建算法以miniSAR卫星成功入轨后的一组定轨数据及根据参考轨道特性解析得到的参考轨道预估值为输入，基于仅考虑中心天体非球形高阶引力摄动的轨道外推模型、Eckstein-Hechler平根模型及嵌套式迭代修正方法，设计输出其任务周期内使用的参考轨道。数值实验表明:所建算法设计的参考轨道生成的参考轨迹在三维空间的回归精度优于0.01 m，满足实际工程应用需求。 

Precise references orbit design of miniSAR satellite

In order to meet the requirements of the mini synthetic aperture radar (miniSAR) satellite interferometry mission for the space baseline, a set of precision reference orbit design algorithms was established by analyzing the features of the satellite reference orbit. The algorithm takes a group of orbit determination data after the successful orbit insertion of the miniSAR satellite and the estimation elements of reference orbit obtained by analyzing the reference orbit features as inputs. The Eckstein-Hechler mean elements model and nested iterative correction method are used to design and output the reference orbit within the mission duration. Numerical simulation shows that the spatial regression accuracy of the reference trajectory formed by the algorithm is better than 0.01 m, which can be applied to real engineering application.