绕飞慢自旋小天体的航天器运动分析  

Spacecraft Motion Analysis about Slowly Rotating Small Body

作　　者：崔祜涛[1] 史雪岩[1] 崔平远[1] 栾恩杰 

机构地区：[1]哈尔滨工业大学深空探测基础研究中心,黑龙江哈尔滨150001 [2]中国国家航天局,北京100037

出　　处：《航空学报》2004年第1期16-20,共5页Acta Aeronautica et Astronautica Sinica

基　　金：国防科工委民用航天计划资助项目。

摘　　要：针对可以用三轴椭球体近似建模的小天体,给出了非球形引力势函数,建立了航天器绕飞小天体的轨道动力学方程。利用Jacobi积分常数绘制了探测器在小天体周围的零速度曲线,并分析了探测器的可能运动区域,给出了航天器不碰撞小天体的边界条件。针对绕飞慢自旋小天体的情况,基于平均轨道根数的近似解分析了小天体扁率和椭率的摄动影响,并给出了几条冻结轨道及其稳定条件。The irregular sphere gravitational potential is given based on adapting to a tri-axial ellipsoid model of a small body, and the spacecraft orbital dynamics equation around a small body is established. According to the integral Jacobi constant, the spacecraft zero-velocity curves in the vicinity of the asteroid are described and feasible motion region is analyzed. Limited condition and periapsis radius corresponding to different eccentricity against impact surface are presented. Perturbation solutions of mean orbit elements are used. Effect of asteroid oblateness and ellipticity is analyzed. Lagrange perturbation equations based on mean orbit elements are used, a few partially frozen orbits are given, and the stability of frozen orbits is analyzed.

关 键 词：慢自旋小天体 零速度曲线 冻结轨道 轨道稳定性 

分 类 号：V529.1[航空宇航科学与技术—人机与环境工程]