| 引用本文: | 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,2014,36(6):60-64.[点击复制] |
| HE Boyong,SHEN Hongxin,LI Haiyang.An improved differential correction method for trans-lunar orbit design[J].Journal of National University of Defense Technology,2014,36(6):60-64[点击复制] |
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| 地月转移轨道设计的改进微分校正方法 |
| 贺波勇, 沈红新, 李海阳 |
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(国防科技大学 航天科学与工程学院， 湖南 长沙 410073)
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| 摘要: |
| 地月转移轨道设计是探月关键技术之一，微分校正法是公认的解决非线性迭代问题的有效方法。针对探月任务中地月转移轨道设计精度高、计算速度快等要求，提出一种改进的微分校正快速设计方法。该方法基于DE405/LE405星历数据下日、地、月和地球J2项摄动真实轨道动力学模型，推导了近月点和入轨点设计参数偏导数关系，在积分轨道状态量的同时积分微分校正矩阵，用积分得到的准确微分校正矩阵求逆，快速迭代得到轨道设计结果。仿真结果表明，利用该方法设计地月转移轨道收敛速度远优于同等精度动力学模型—序列二次规划算法。 |
| 关键词: 月球探测 转移轨道 轨道设计 微分校正法 |
| DOI：10.11887/j.cn.201406011 |
| 投稿日期：2014-05-19 |
| 基金项目:国家自然科学基金资助项目（11372345,11402295） |
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| An improved differential correction method for trans-lunar orbit design |
| HE Boyong, SHEN Hongxin, LI Haiyang |
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(College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)
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| 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. |
| Keywords: lunar probe transfer lunar orbit orbit design differential correction method |
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