摘要
研究绳系卫星系统质心沿椭圆轨道运动时,子星释放的最佳初始条件,运用变量替代简化动力学控制方程;对圆轨道运动的母星,采用轨道转移方法释放子星,计算弹射变轨参数及过渡轨道终了真近点角.本文取消母星质量远大于子星质量的假设,考虑子星释放过程中绳系卫星系统质心随子星运动的变化,所得结果更具有普遍意义.数值模拟结果表明,所述方法的有效性.
This paper investigates the ejection of tethered satellite systems. For the deployment of a tethered satellite from an elliptical orbit, the initial angle and velocity of the ejection that minimizes final errors are evaluated, and the dynamic equations are simplified with variable transformation. The method of orbital transfer is utilized for the deployment of a tethered satellite from a circular orbit. The parameters of orbit transformation are given, and the true anomaly is calculated at the end of transforming orbit. In many literatures, it is supposed that the mass of the spacecraft is far greater than that of the payload, so it is further supposed that the center of mass of the tethered satellite system coincides with that of the spacecraft. Those assumptions are only correct for that the spacecraft is massive, such as a space shuttle or a space station. In this paper, there is no assumption that the mass of the spacecraft is far greater than that of the payload, so the conclusions are more general. The numerical simulation results are presented and show that the method is really effective.
出处
《空间科学学报》
CAS
CSCD
北大核心
2002年第3期282-288,共7页
Chinese Journal of Space Science
基金
国家自然科学基金资助项目(19872032)
