基于地球引力变轨的日冕探测器轨道设计

Design of Earth Gravity Assist Trajectories for the Coronal Mass Ejections Probe

研究了相对黄道面有一定倾角的探测器轨道设计的问题。以金星借力轨道设计为例,分析了轨道偏心率与轨道倾角增量之间的关系。根据C3匹配原理搜索了“地球-中间天体-地球”多天体交会的发射窗口。最后,设计了与地球轨道周期相等的三次地球借力轨道,该轨道倾角可以达到黄纬30°以上。理论分析及仿真结果表明:基于地球引力设计此类轨道时,应采用多天体交会方案,才能既保证地球逃逸能量低,又保证首次飞入地球影响球前轨道偏心率较大的双重指标;同时应采用多次地球借力方案,该方案具有每次借力后轨道偏心率逐渐减小的特点,当其减小到零时,再次借力后轨道倾角不会继续增加。

This paper designed trajectories that are inclined to near-sun, high-inclination mission. Taking the design of Venus gravity - assist trajectories as an example, the relation between orbital eccentricity and orbital inclination was analyzed. The launch opportunities for Earth-Venus-Earth and Earth-Venus-Mars-Earth were searched based on the principle of energy equation. Final- ly, multiple Earth gravity assist trajectories were designed, a 30deg-inclination of the trajectory with respect to the solar equator was obtained after a 3-year-long. The results indicate that the orbital eccentricity, which is before the first Earth-gravity assist, should be as large as possible to get a high-inclination, the multiple plants gravity assist flybys ensure a large eccentricity before the first Earth-gravity assist, and ensure a small launch energy, the inclination will increase little when the eccentricity approaches zero.