考虑地球扁率的大椭圆轨道编队飞行优化设计

J_2 Optimization Design of Formation Satellites in Highly Elliptic Orbits

大椭圆轨道上卫星编队的相对运动特性及其所受摄动力的影响给编队轨道设计者提出了新的挑战。本文总结了大椭圆轨道卫星编队的五种基本形式,利用数值积分法计算了主星轨道倾角、近地点角和平近点角初值对地球扁率作用下基本编队形式相对位置极值点漂移量的影响规律。结合零J2项摄动条件,提出基于主星平近点角初值的J2项编队相对轨道优化设计方法,进而获得瞬时根数描述的编队初始条件。仿真算例表明:优化设计结果可以明显降低大椭圆轨道编队卫星的相对漂移量,与平根数描述的编队初始条件的设计结果相比,相对距离极大值点的漂移量降低约81.8681%,验证了基于主星平近点角初值的大椭圆轨道编队优化设计方法的可行性。

The perturbed relative motion of satellite clusters on highly eccentric orbits makes orbit designers face a new challenge. The mathematic models of five basic formation modes are presented, in which all the satellites run along highly elliptic orbits. Then, how the initial mean anomaly of chief satellite affects those basic modes is calculated numerically in view of J2 perturbation, as well as its inclination and argument of perigee. On the basis of it, the formation optimization design by choosing the initial mean anomaly is brought forward to protect satellites from separating due to J2 . The method also can be combined with J2 invariant conditions and be described by osculating orbit elements. Finally, the resuhs indicate that the formation drifts are greatly reduced with the optimized initial mean anomaly. And the drift of formations set up in osculating elements is decreased by 81.8681 percent, compared with that in mean elements, which proves the feasibility of this optimization design.