基于三体系统平动点轨道的环日全景任务轨道设计

在空间开展太阳观测是研究太阳活动周、太阳爆发、极端天气等事件起源的重要手段。环日全景探测计划是为实现从黄道面360°全方位观察太阳行星际空间而提出的。本文针对环日全景探测计划，构建了基于三体系统平动点低能量轨道的环日全景轨道部署方法。该方法以日–地L1/L2点Halo轨道幅值及Halo轨道离轨点为变量，以转移轨道飞行时间、入轨机动大小为评价指标，基于三体系统不变流形构建环日全景的转移轨道，并开展轨道优化设计。采用等高线图对设计变量及任务成本进行全局分析。仿真计算表明，轨道部署无法同时满足飞行时间最短与入轨机动最小的要求。设计了轨道机动约束条件下的最优飞行时间解，并给出了基于长三甲运载火箭的一箭双星发射及入轨方案。 

Trajectory Design of Solar Ring Mission Based on Libration Point Trajectory of Three-body System

Solar observations in space are the key means to understand the origin of solar cycles, solar eruptions, and extreme weather events. In order to observe the Sun from the ecliptic plane at 360 degrees, scientists have proposed a 3D solar exploration mission. Aiming at the “Solar Ring” mission, a deployment method of “Solar Ring” orbit based on the low-energy trajectories associated with the libration point of the three-body system is proposed. Using the amplitude and off-orbit points of Sun-Earth L1/L2 Halo orbits as design parameters, the transfer time and deep-space maneuver as the cost function, the mission trajectories are constructed and optimized with the invariant manifolds of three-body system and contour maps. A global analysis of mission cost and the corresponding design variables is carried out. Simulation results show that the orbit deployment cannot satisfy the shortest transfer time and the smallest deep-space maneuver at the same time. The optimal transfer time solution under the orbit maneuver constraint is obtained, and a plan for launching and deploying orbits is designed based on the way of one rocket two spacecraft with the rocket of Long Match 3A.