卫星编队飞行的动力学特性与相对轨道构形仿真

为了克服 Hill方程的局限性 ,利用轨道根数描述卫星编队飞行 ,从理论上给出了长期编队所需的条件 ,包括相对位置和相对速度的关系 ,以及和各卫星相对轨道根数之间的关系 ;理论上证明了要长期近距离编队卫星轨道周期必须相同。仿真了各种不同轨道根数下的相对运动轨迹 ,与定性的理论分析进行比较 ,说明了轨道根数描述方法的优越性。方法可适用任意偏心率的椭圆轨道 ,将为飞行器编队飞行的轨道设计提供理论参考。不考虑摄动时轨道根数接近的飞行器不需主动控制而可长期保持近距离编队飞行

Dynamics behavior and simulation of relative trajectories of satellite formation flying

To overcome the restriction of Hill's equation, this paper presents the orbital elements method for describing the relative motion of satellite formation flying. Theoretical conditions are derived for long term formation flying that includes the relationship between the relative distances and velocities and the relative orbital elements. The analysis proves that the orbital periods of formatted satellites must be equal. Simulation of the relative trajectories with various orbital elements and a qualitative theoretical analysis illustrate the advantages of the orbital elements method. The proposed method can be used for large eccentricity elliptical orbits and can be applied for orbit design of spacecraft formation flying. The results show that satellites formatted using closed orbital elements will remain in their orbits with little active control. The theoretical results show that the application of Hill's equation is restricted to short time formation flying in circular orbits.