Trajectory Design of Solar Ring Mission Based on Libration Point Trajectory of Three-body System
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摘要: 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。Abstract: 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.
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Key words:
- Solar ring mission /
- Low-energy orbit /
- Invariant manifolds /
- Low-cost deployment
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图 3 基于不变流形的环日全景部署轨道优化设计方法
Figure 3. Flowchart of the design method for Solar Ring mission trajectory based on invariant manifolds
图 11 轨道机动≤0.75 km·s–1区域的飞行时间等高线
Figure 11. Contour map of flight time corresponding to phasing maneuver less than 0.75 km·s–1
图 12 日地旋转坐标系中的最优飞行轨道
Figure 12. Optimal transfer trajectories with constrained phasing maneuver in the Sun-Earth rotation system
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[1] FARQUHAR R W. Lunar communications with libration-point satellites[J]. Journal of Spacecraft and Rockets, 1967, 4(10): 1383-1384 doi: 10.2514/3.29095 [2] FARQUHAR R W, MUHONEN D P, NEWMAN C R, et al. Trajectories and orbital maneuvers for the first libration-point satellite[J]. Journal of Guidance and Control, 1980, 3(6): 549-554 doi: 10.2514/3.56034 [3] DUNHAM D W, FARQUHAR R W. Libration Point Missions, 1978–2002[M]. Singapore: World Scientific, 2003 [4] 魏海燕, 范全林, 时蓬. 欧美发射太阳轨道探测器推动抵近太阳观测[J]. 空间科学学报, 2020, 40(2): 147-150WEI H Y, FAN Q L, SHI P. Europe and the United States launch solar orbiters for the Sun observation[J]. Chinese Journal of Space Science, 2020, 40(2): 147-150 [5] CASE A W, KASPER J C, STEVENS M L, et al. The solar probe cup on the Parker solar probe[J]. The Astrophysical Journal Supplement Series, 2020, 246(2): 43 doi: 10.3847/1538-4365/ab5a7b [6] 季海生, 汪毓明, 汪景琇. 太阳的立体观测[J]. 中国科学: 物理学 力学 天文学, 2019, 49(5): 059605JI Haisheng, WANG Yuming, WANG Jingxiu. Stereoscopic observations of the Sun[J]. Scientia Sinica-Physica, Mechanica & Astronomica, 2019, 49(5): 059605 [7] 郑建华, SPORT任务论证组. 太阳风太阳极轨成像仪任务概念设计[C]//中国空间科学学会第七次学术年会会议手册及文集. 大连: 中国空间科学学会, 2009: 32-32Zheng J H, SPORT Project Demonstration Group. Solar wind solar polar orbit imager task concept design[C]// Proceedings of the 7 th Annual Conference of the Chinese society of space research. Dalian: Chinese society of space research, 2009: 32-32 [8] WANG Y M, JI H S, WANG Y M, et al. Concept of the solar ring mission: an overview[J]. Science China Technological Sciences, 2020, 63(9): 1699-1713 doi: 10.1007/s11431-020-1603-2 [9] WANG Y M, CHEN X, WANG P C, et al. Concept of the Solar Ring mission: preliminary design and mission profile[J]. Science China Technological Sciences, 2021, 64(1): 131-138 doi: 10.1007/s11431-020-1612-y [10] GÓMEZ G, JORBA A, MASDEMONT J, et al. Study of the transfer from the Earth to a halo orbit around the equilibrium point L1[J]. Celestial Mechanics and Dynamical Astronomy, 1993, 56(4): 541-562 doi: 10.1007/BF00696185 [11] KULUMANI S, LEE T. Systematic design of optimal low-thrust transfers for the three-body problem[J]. The Journal of the Astronautical Sciences, 2019, 66(1): 1-31 doi: 10.1007/s40295-018-00139-y [12] ZENG H, ZHANG J R. Design of impulsive Earth-Moon Halo transfers: lunar proximity and direct options[J]. Astrophysics and Space Science, 2016, 361(10): 328 doi: 10.1007/s10509-016-2888-8 [13] LEI H L, XU B. Resonance transition periodic orbits in the circular restricted three-body problem[J]. Astrophysics and Space Science, 2018, 363(4): 70 doi: 10.1007/s10509-018-3290-5 [14] KATO M, SASAKI S, TANAKA K, et al. The Japanese lunar mission SELENE: science goals and present status[J]. Advances in Space Research, 2008, 42(2): 294-300 doi: 10.1016/j.asr.2007.03.049 [15] LO M W, WILLIAMS B G, BOLLMAN W E, et al. Genesis mission design[J]. The Journal of the Astronautical Sciences, 2001, 49(1): 169-184 doi: 10.1007/BF03546342 [16] 孟林智, 黄江川, 叶培建, 等. 嫦娥二号卫星多目标多任务设计与经验[J]. 中国科学: 技术科学, 2013, 43(6): 585-595Meng L Z, HUANG C J, YE J P, et al. Multi-objectives and multi-missions design and experience of Chang'E-2 satellite[J]. Scientia Sinica: Technologica, 2013, 43(6): 585-595 [17] SZEBEHELY V. Theory of Orbits: the Restricted Problem of Three Bodies[M]. New York: Academic Press, 1967 [18] RICHARDSON D L, CARY N D. A uniformly valid solution for motion about the interior libration point of the perturbed elliptic-restricted problem[C]//Proceedings of the AIAA/AAS Astrodynamics Specialists Conference. Nassau, Bahamas: AIAA/AAS, 1975: 75-021 -
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