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月面返回最优轨道设计

Optimal Orbit Design of Returning from Moon

【作者】 李罗刚

【导师】 崔祜涛;

【作者基本信息】 哈尔滨工业大学 , 飞行器设计, 2010, 硕士

【摘要】 随着航天科技的发展,人类对月球的探索正在日益深入,而我国的探月工程也正在有序而顺利的实施中。月面返回技术是月球探测的一项关键技术,而如何设计返回轨道,如何使返回过程实现燃料消耗尽可能小,成为我国探月工程三期必须要解决的问题。本文首先对月面返回动力上升段的轨道进行探讨。主要针对航天器月面返回动力上升段燃料消耗问题,综合考虑月球自转,科里奥利力的影响,建立航天器在月球三维空间中的动力学模型。以燃耗最优为指标,利用pontryagin极大值原理,得到航天器在月面返回动力上升段发动机推力方向的最优开环控制律。考虑终点位置和速度约束求解共轭变量初值,最终求得可行的航天器最优轨迹。本文还对月地转移轨道的相关特性进行了分析和设计。首先在基于月球影响球概念的三维模型下对月地转移轨道有关特性进行了初步的分析。然后对月地转移轨道轨道进行了初步的设计方法研究。最后在分析了各主要摄动力的作用后,在比较精确的动力学模型中进行了月地转移轨道设计。

【Abstract】 With the development of aerospace science and technology, the exploration to moon is carried frequently and in deep, and the lunar exploration program of our country has been implementing smoothly and orderly. Returning from the moon is a key technology for the moon exploration, and how to reduce the fuel consumption in the process has become the crucial problem must be resolved in China’s lunar exploration third stage program.Firstly,this article discusses the orbit of the section of the lunar surface back to power up. Face the problem of fuel consumption, considering influence factor of rotation of moon and geostrophic force, precise three dimensional dynamics for lunar probe returning from the moon were presented. To realize the minimal fuel strategy , an optimal control law of the thrust direction was proposed based on the maximum principle. Solving it concerning both velocity and position restrictions, the optimal orbit of returning from the moon was obtained. The research result is valuable to engineering application.The article also analyze the nature of transfer orbit from moon to earth. Firstly, use the concept of the impacting ball of the moon, in the 3D space, analyze the property of transfer orbit. Through computer simulation, we obtained some of the main parameters correlation curve, finally, Secondly, propose a fast search algorithm for moon-earth transfer orbit; Finally, through the analysis of the effectiveness of each main disturbing force, design the moon-earth transfer orbit with the precisely dynamical model.

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