摘要
研究了太阳帆日心移位轨道的稳定性、控制律设计及轨道拼接。将柱坐标形式的太阳帆动力学方程在参考移位轨道附近线性化,得到线性变分方程。分析线性变分方程的特征值在复数平面上的位置就可以得到移位轨道的稳定性条件。设计了太阳帆日心移位轨道的控制律,并证明了控制律满足稳定性条件。该控制律仅要求太阳帆在移位轨道飞行时姿态角α保持不变。此外,太阳帆移位轨道可以与开普勒轨道相互转化,也可以与移位轨道之间相互拼接。
The issues of solar sail spacecraft Sun-centred displaced orbit stability, control and patch are studied. By linearizing the model along the nominal orbit, the linear variational equation is deduced. The stability characteristics of the displaced orbit can be investigated by analyzing ei- genvalues in the complex plane. The control law of solar sail Sun-centred displaced orbit is de- signed and proved stable. This control law only requires attitude angle a keeping fixed. Besides, Sun-centred displaced orbits can be patched to Keplerian orbits, and also can be patched together.
出处
《航天器工程》
2012年第6期25-29,共5页
Spacecraft Engineering
基金
太阳帆民用航天资助项目
航天飞行动力学技术重点实验室开放基金资助项目(2012afdl028)
关键词
太阳帆
移位轨道
稳定性
控制律
轨道拼接
solar sail
displaced orbit ~ stabiiity~ control law~ patched orbit
