基于智能优化算法的转移轨道优化设计
发布时间：2018-08-09 11:23
【摘要】：在当今世界,航天事业是衡量一个国家科技水平的重要标志。航天事业的发展是复杂而又艰难的,它涉及的领域几乎遍布各个行业范围,越来越受到广泛的关注。空间交会技术与天地往返技术、太空行走技术并列为载人航天三大重要技术,由此可见其在航天技术之中的重要性。尽管各国已经多次完成了交会对接任务,然而由于其本身的复杂性和高风险的本质,尚不能说这项技术已经成熟。另外由于航天事业的高成本、高消耗,如何设计变轨过程以达到节省燃料和减少转移时间等目的也是很值得研究和探讨的。本文针对航天交会理论的Lambert问题进行了详细阐述。同时,根据航天器的轨道根数和速度及位置矢量在地球惯性坐标系下进行轨道建模,分别采用枚举法、遗传算法和和声搜索算法三种智能优化算法对轨道进行优化设计,对三种不同前提进行了深入研究,主要研究内容包括以下几个方面。首先,建立轨道优化问题的数学模型及目标和飞行器的动力学模型。为清晰描述航天器交会过程,首先介绍了卫星的二体问题、轨道根数等基础知识。并建立了轨道根数和速度矢量及位置矢量的转换式,为后续的Lambert问题分析及轨道优化设计奠定基础。其次,针对航天交会中的异面转移Lambert问题,分别采取三种方法:半长轴迭代的二分法、Battin-Vaughan算法和曲线交点提取法求解Lambert问题。阐述了三种算法的核心思想和求解步骤。利用两个算例仿真验证了三种算法的有效性,并对三种算法的效率和精确性进行了比较分析得出结论。最后,对转移轨道优化问题依次从参数的选取、目标函数的定义、约束条件的分析、优化算法的选择四个方面依次展开。首先分析空间约束条件,分别研究真近点角和转移时间对燃料消耗的影响。分别以燃料消耗和转移时间为优化指标对转移轨道交会系统进行单目标和多目标优化设计。分别采用枚举法、遗传算法和和声搜索算法作为主要优化方法,阐述三种方法的核心思想和设计思路,结合过程约束,对三种优化算法仿真验证了准确性,并对三种方法进行了比较研究,为异面椭圆的转移轨道优化设计提供参考和决策依据。
[Abstract]:In today's world, aerospace is an important symbol of a country's scientific and technological level. The development of aerospace industry is complex and difficult. Space rendezvous technology, space walking technology and space walking technology are three important technologies of manned spaceflight, which shows their importance in spaceflight technology. Although rendezvous and docking missions have been completed many times, the technology cannot be said to be mature due to its complexity and high risk nature. In addition, because of the high cost and high consumption of the aerospace industry, how to design the orbit transfer process to save fuel and reduce the transfer time is also worth studying and discussing. In this paper, the Lambert problem of space rendezvous theory is discussed in detail. At the same time, according to the orbit root number, velocity and position vector of the spacecraft, the orbit is modeled in the earth inertial coordinate system. Three intelligent optimization algorithms, enumeration method, genetic algorithm and harmony search algorithm, are used to optimize the orbit design. Three different premises are studied in depth, the main research contents include the following aspects. Firstly, the mathematical model of orbit optimization problem and the dynamic model of target and vehicle are established. In order to describe the process of spacecraft rendezvous clearly, the basic knowledge of satellite two-body problem, orbital root number and so on is introduced. The transformation formula of orbit root number, velocity vector and position vector is established, which lays a foundation for the following Lambert problem analysis and orbit optimization design. Secondly, aiming at the cross-plane transfer Lambert problem in the rendezvous, three methods are adopted: the semi-long-axis iterative dichotomy and the curve intersection extraction method to solve the Lambert problem. The core idea and solving steps of the three algorithms are expounded. The effectiveness of the three algorithms is verified by two examples, and the efficiency and accuracy of the three algorithms are compared and analyzed. Finally, the optimization problem of transfer orbit is developed from four aspects: the selection of parameters, the definition of objective function, the analysis of constraint conditions, and the selection of optimization algorithm. Firstly, the space constraint conditions are analyzed, and the effects of true proximity angle and transfer time on fuel consumption are studied respectively. The single objective and multi-objective optimization design of the transfer orbit rendezvous system is carried out with the fuel consumption and transfer time as the optimization index respectively. The enumeration method, genetic algorithm and harmony search algorithm are used as the main optimization methods respectively. The core ideas and design ideas of the three methods are expounded. The accuracy of the three optimization algorithms is verified by the simulation of the three optimization algorithms combined with the process constraints. The three methods are compared and studied to provide the reference and decision basis for the optimal design of the transfer orbit of the cross-plane ellipse.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V412.41
本文编号：2173921
[Abstract]:In today's world, aerospace is an important symbol of a country's scientific and technological level. The development of aerospace industry is complex and difficult. Space rendezvous technology, space walking technology and space walking technology are three important technologies of manned spaceflight, which shows their importance in spaceflight technology. Although rendezvous and docking missions have been completed many times, the technology cannot be said to be mature due to its complexity and high risk nature. In addition, because of the high cost and high consumption of the aerospace industry, how to design the orbit transfer process to save fuel and reduce the transfer time is also worth studying and discussing. In this paper, the Lambert problem of space rendezvous theory is discussed in detail. At the same time, according to the orbit root number, velocity and position vector of the spacecraft, the orbit is modeled in the earth inertial coordinate system. Three intelligent optimization algorithms, enumeration method, genetic algorithm and harmony search algorithm, are used to optimize the orbit design. Three different premises are studied in depth, the main research contents include the following aspects. Firstly, the mathematical model of orbit optimization problem and the dynamic model of target and vehicle are established. In order to describe the process of spacecraft rendezvous clearly, the basic knowledge of satellite two-body problem, orbital root number and so on is introduced. The transformation formula of orbit root number, velocity vector and position vector is established, which lays a foundation for the following Lambert problem analysis and orbit optimization design. Secondly, aiming at the cross-plane transfer Lambert problem in the rendezvous, three methods are adopted: the semi-long-axis iterative dichotomy and the curve intersection extraction method to solve the Lambert problem. The core idea and solving steps of the three algorithms are expounded. The effectiveness of the three algorithms is verified by two examples, and the efficiency and accuracy of the three algorithms are compared and analyzed. Finally, the optimization problem of transfer orbit is developed from four aspects: the selection of parameters, the definition of objective function, the analysis of constraint conditions, and the selection of optimization algorithm. Firstly, the space constraint conditions are analyzed, and the effects of true proximity angle and transfer time on fuel consumption are studied respectively. The single objective and multi-objective optimization design of the transfer orbit rendezvous system is carried out with the fuel consumption and transfer time as the optimization index respectively. The enumeration method, genetic algorithm and harmony search algorithm are used as the main optimization methods respectively. The core ideas and design ideas of the three methods are expounded. The accuracy of the three optimization algorithms is verified by the simulation of the three optimization algorithms combined with the process constraints. The three methods are compared and studied to provide the reference and decision basis for the optimal design of the transfer orbit of the cross-plane ellipse.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V412.41
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