国防科技大学学报Issue(6)：60-64,5.DOI:10.11887/j.cn.201406011
地月转移轨道设计的改进微分校正方法
An improved differential correction method for trans-lunar orbit design
摘要
Abstract
Designing the trans-lunar orbit is one of the key skills for lunar probe mission,and the differential correction is proved to be one of the effective methods to solve a non-linear iteration equation.According to the requirements of high design precision and rapid calculation speed in designing the trans-lunar orbit,a rapid trans-lunar orbit design method from improved differential correction was proposed.Based on the dynamical model,which contains the sun,the earth,the moon,and the earth's J2 perturbation force in the DE405 /LE405 planet and lunar-ephemeris data, the partial derivative matrix of parameters from the perilune to the perigee was deduced.The differential correction matrix was integrated in company with the orbital state variables and velocity,and the transfer orbit design parameters were converged iteratively and rapidly with the precise differential correction matrix.Simulation result shows that the convergence rate of the integral differential correction method is faster than the frequently-used SQP(Sequential Quadratic Programming)method in dynamical models with the same accuracy.关键词
月球探测/转移轨道/轨道设计/微分校正法Key words
lunar probe/transfer lunar orbit/orbit design/differential correction method分类
航空航天引用本文复制引用
贺波勇,沈红新,李海阳..地月转移轨道设计的改进微分校正方法[J].国防科技大学学报,2014,(6):60-64,5.基金项目
国家自然科学基金资助项目 （）
