火星探测直接转移轨道精确求解研究

Research on Precise Design of the Mars Probe Ballistic Trajectory

针对火星探测直接转移轨道精确求解问题,提出了一种快速微分修正算法.基于二体模型建立控制参数和目标参数偏差关系的数学模型,并由此求解系统的偏导数矩阵;采用B平面参数作为中间变量,对算法进行两层迭代设计,有效地减少了求解过程中的积分运算次数.以2018年火星探测机会为例对算法进行了验证,仿真结果表明,利用圆锥曲线拼接法得到的轨道初值,求解一条标准轨道只需6～9次积分迭代.通过STK对计算结果进行了对比和验证.

This paper studies the problems of precise design of the Mars probe ballistic trajectory. A fast differential correction algorithm is given.The model of the relationship between the difference of the independent and dependent variables is formulated using the two-body equations,by which the partial derivatives matrix can easily be calculated.Using the impact parameter B as mid variables, the algorithm is designed to be a two-layer iterative procedure,which can notably reduce the times of orbit propagation computations.Taking the 2018 Mars probe opportunity as an example,the algorithm is demonstrated and verified.The result proved that,using the initial value got by the Patched-Conic approach,only 6～9 orbit propagation procedures are needed to find a precise orbit. The numerical results are verified using STK（Satellite Tool Kit）.