近圆轨道编队飞行星座相对构型稳定性分析

Stability Analysis for Relative Configuration of Spacecraft Formation Flying

在近圆轨道编队飞行的假设条件下 ,根据动力学关系推导出了环绕卫星相对参考卫星的运动学简化模型 ,并以此简化模型为基础 ,研究了半长轴入轨偏差δa ,轨道倾角偏差δi ,轨道偏心率偏差δe在地球扁率摄动条件下对编队飞行星座相对构型稳定性影响 ,深入分析了各种因素的规律和特点 ,并以此对编队飞行星座轨道设计提出建议。

According to kinematic relationship, simplified motion equations of surrounding satellite with respect to reference satellite is deduced under near circle orbit of formation flying assumption. Then based on this simplified motion equations, it's discussed that how semimajor axis of orbit error δ -a , inclination of orbit error δ -i and eccentricity of orbit error δ -e affect stability of relative configuration of spacecraft formation flying. Finally some suggestion are presented to the orbit design of formation flying.