基于逼近理想解排序法的航天器初始轨道选优  

An Approach to Optimizing the Initial Orbital Elements of Spacecraft Base on TOPSIS Method

作　　者：杨永安[1] 冯祖仁[1] 张宏伟[2] 吴云鹤[2] 

机构地区：[1]西安交通大学,西安710049 [2]西安卫星测控中心,西安710043

出　　处：《宇航学报》2006年第4期700-703,719,共5页Journal of Astronautics

基　　金：航天器轨道确定技术研究(装字第3255号)

摘　　要：针对航天器入轨段,如何从多组初始轨道中选择一组最优或最符合客观实际轨道根数问题,进行了深入地理论分析,提出了基于逼近理想解排序法的航天器初始轨道根数选优算法。描述了逼近理想解排序法的设计思想以及求解的六个基本步骤;针对航天器初始轨道的设计特点,巧妙地利用标称轨道作为理想解,偏差轨道作为负理想解,成功地应用逼近理想解排序法建立了初始轨道根数选优的决策数学模型,并以一颗典型的太阳同步轨道卫星为例,验证了其数学模型和选优算法的合理性和正确性。This paper discusses the problem in theory how to select the optimal or satisfying one among many sets of initial orbital elements, which are obtained from different kinds of facilities during spacecraft injection phase, and presents a new approach about optimization of initial orbital elements, which is based on the TOPSIS （Technique for Order Preference by Similarity to Ideal Solution） method. The design idea and six basic solution step of TOPSIS are described. According to the feature of spacecraft initial orbit, a decision-making mathematical model on optimization of initial orbital is established successfully by assuming the normal orbit as ideal solution and the bias orbit as negative-ideal solution. A optimization procedure of initial orbital elements is illustrated by a typical sun-synchronous satellite, and then the rationality and correctness of the mathematical model and optimizing method are verified.

关 键 词：系统工程 逼近理想解排序法 航天器 初始轨道 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]