航天飞行器轨道动力学与控制

ORBIT DYNAMICS AND CONTROL OF SPACEFLIGHT

空间探索飞行器的轨道设计与控制是保证飞行器顺利完成探索任务的关键问题之一。本文用矢量法、极坐标法、直角坐标法导出航天飞行器的轨道方程，研究了飞行器的飞行轨道随初始条件的变化关系，为高、深空间探索奠定了理论基础。

The orbit design and control of space explorations are one of the key problems in guaranteing spacecraft successfully completing exploration mission.Using vector method,polar coordinate method and rightangled method,this paper derives the orbit equation of spacecraft and investigates the control method.It establishes the theoretical basis for deep space exploration.