Firstly, based on simplified dynamics of lunar soft landing, an explicit guidance law was induced by solving the special two-point boundary value problem.
首先，基于简化的软着陆动力学模型，通过求解特殊两点边值问题，给出了一种实时显式制导方法。
On Jan. 9, 1968, the Surveyor 7 space probe made a soft landing on the moon, marking the end of the American series of unmanned explorations of the lunar surface.
1968年1月9日，测量员7号空间探测器在月球表面软着陆，标志着美国对月球表面的无人探测系列任务的结束。
Based on minimal fuel principle, the switching curve of ignition is confirmed by using optimization theory, and a braking scheme is designed for the process of the lunar probe vertical soft landing.
针对月球探测器垂直软着陆过程，基于耗燃最优的原则，利用最优化理论确定了点火切换曲线。设计出一种制动方案。
Thrusters were used as the main attitude control actuators for the whole process of the lunar soft landing.
月球探测器在近月点下降全过程，控制系统主要采用推力器为执行机构。
A method of applying parametric control and enhancing technique in order to solve optimal control problem of lunar probe precise Fixed-point soft landing is studied.
研究了一种应用参数化控制求解月球探测器精确定点软着陆最优控制问题的方法。
In the second stage of Chinese lunar exploration project, soft landing of the lunar explorer on the lunar surface is to be realized.
在我国“嫦娥计划”的二期工程中，要实现月球探测器软着陆于月球表面。
To achieve the soft landing on a specified region of lunar surface, the paper studies a linear quadratic optimal guidance method for lunar soft landing.
为实现在月球表面指定区域的精确软着陆，研究了月球软着陆的线性二次型最优制导方法。
For the needs of lunar soft-landing simulation system, using the com component technology, the paper designs the lunar soft-landing architecture based on HLA.
针对月球软着陆仿真任务的需求，采用COM组件技术，设计基于HLA的月球软着陆仿真系统的体系结构。
A method of applying nonlinear program to solve optimal control problem of lunar probe soft landing under finite thrust is studied.
研究了一种应用非线性规化求解有限推力作用下月球探测器软着陆最优控制问题的方法。
To improve the analysis accuracy of soft landing impact response for lunar lander, a method based on nonlinear transient dynamic analysis was presented.
为提高分析月球着陆器软着陆有效载荷着陆冲击响应的准确性，提出一种基于瞬态动力学的着陆器有效载荷软着陆冲击响应分析方法。
Therefore, the direct collocation method is a viable approach to lunar probe soft landing trajectory optimization problem.
因此，直接配点法对于再入轨迹优化问题的求解是可行的。
The problem of rapid Lunar soft-landing trajectory optimization by using a Legendre pseudospectral method was studied in this paper.
研究了伪光谱方法在空间飞行器有限推力轨道转移最优化问题中的应用。
The problem of rapid Lunar soft-landing trajectory optimization by using a Legendre pseudospectral method was studied in this paper.
研究了伪光谱方法在空间飞行器有限推力轨道转移最优化问题中的应用。
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