满足约束条件的月球卫星飞行轨道的初步设计

Lunar Satellite Trajectory Designing Under Certain Constraints

讨论满足约束条件的月球卫星飞行轨道的设计问题．将约束条件分类为只与太阳、月球、地球、飞行器和观测站之间的相对位置有关的运动学约束条件以及涉及到飞行器轨道运动的动力学约束条件．在考虑月球卫星飞行轨道的受力情况后，给出一种准确快速地计算和设计满足约束条件的标准飞行轨道的方法，并应用于不同约束条件下月球卫星的轨道预设计．初步讨论了轨道设计的误差分析、轨道跟踪及实时精密定轨等正在进行的其它相关工作。

We present a method to design trajectory for a Lunar satellite under certain constraints. The constrains are classified into two categories. Kinetic constraints deal with the relative configurations among Sun, Lunar, Earth spacecraft and tracking stations, while the dynamic constrains concern the orbit of the spacecraft. The models to compute the trajectory under precision requirement and a method to search for a standard trajectory satisfying the constraints are developed in this paper j and are a pplied to the designing for a potential Chinese Lunar mission. Other relevant issues of importance such as the accuracy assessment, tracking and real time orbit determination are under research and the general ideas are introduced in this paper.