摘要
由于空间站的运行轨道在惯性空间是已经确定的,因此对于基于空间站组装的月球探测器,需要对其奔月轨道做出专门设计。本文结合月球的运动规律,建立了完整的奔月轨道数学模型,并结合工程的实际背景,给出了相应的约束条件,从而将轨道设计问题转化为求解满足一系列约束条件的轨道动力学方程。然后通过选取合理的优化目标和约束参数,利用遗传算法和SQP算法进行求解,计算得到了满足条件的奔月轨道参数。最后,将得到的初步设计结果,与STK计算结果进行了比较,进一步验证了结论的正确性。
Because of the fixed orbit of the space station in inertia space, it is important to design the trans-lunar trajectory of the probe based on the space station assembly. In this paper, considering the kinematic law of the moon, an integrated mathematical model for trans-lunar trajectory design is established, and the constraint conditions are presented according to practical situations in engineering. Then the main problem for orbit design is to solve the orbit dynamics equation in some constraint conditions. Appropriate object function and constraint conditions are chosen, and the equation is solved by using genetic algorithm and SQP method. The parameters of trans-lunar trajectory are calculated by using numerical method. Finally, by a comparison with the data gained from STK, the results are validated.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2009年第2期25-30,共6页
Journal of National University of Defense Technology
关键词
地球停泊轨道
轨道设计
约束条件
优化目标
STK
earth parking orbit
orbit design
constraint condition
optimization objective
STK
