基于迭代修正方法的严格回归轨道设计

通过分析太阳同步回归轨道的轨道根数和星下点经度/纬度的关系，推导了一组轨道根数的修正公式。基于高精度轨道动力学模型和升交点位置确定方法，构造了关于轨道半长轴和轨道倾角的迭代修正方法。针对偏心率矢量的动力学系统所具有的极限环特性，构造了平均法求其解析近似，从而实现冻结轨道特性对偏心率和近地点幅角的迭代修正。结合迭代修正，得到一组严格回归的轨道根数。该轨道能够重访空间目标点，具有较高的回归精度。

Design of Strictly Regressive Orbit Based on Iterative Adjustment Method

An adjustment formulation of orbit elements of sun-synchronous regressive orbit is investigated based on relationships between orbit elements and the longitude/latitude of nadir points. By applying high precision orbit dynamic and position sampling method of ascending node, an iterative adjustment method of semi-major axis and inclination is designed. A numerical average method is proposed to seek the approximate solutions of limit cycles of eccentricity-vector dynamic system, which realizes the iterative adjustments of eccentricity and argument of perigee for the requirement of frozen orbit. By combining the iterative adjustments, the orbit elements of strictly-regressive orbit are achieved. The resulting orbit can revisit the space target with high regressive accuracy.