基于改进多圆锥截线的月地返回轨道快速设计方法

doi:10.3969/j.issn.1001-506X.2020.04.21

系统工程与电子技术 ›› 2020, Vol. 42 ›› Issue (4): 896-903.doi: 10.3969/j.issn.1001-506X.2020.04.21

基于改进多圆锥截线的月地返回轨道快速设计方法

杨路易(), 李海阳(), 张进(), 周晚萌(), 陆林()

国防科技大学空天科学学院, 湖南长沙 410073

收稿日期:2019-09-16 出版日期:2020-03-28 发布日期:2020-03-28
作者简介:杨路易(1995-),男,博士研究生,主要研究方向为载人登月轨道设计。E-mail:single_yang@foxmail.com|李海阳(1972-),男,教授,博士,主要研究方向为载人航天系统与仿真。E-mail:lihaiyang@nudt.edu.cn|张进(1983-),通信作者,男,副教授,博士,主要研究方向为载人航天系统分析与仿真。E-mail:zhangjin@nudt.edu.cn|周晚萌(1990-),男,博士研究生,主要研究方向为载人登月任务规划。E-mail:zhouwanmeng@163.com|陆林(1996-),男,硕士研究生,主要研究方向为载人登月轨道设计。E-mail:1540834849@qq.com
基金资助:
国家自然科学基金(11572345);载人航天预先研究项目(010201)

Fast Moon-to-Earth return orbit design based on improved multi-conic method

Luyi YANG(), Haiyang LI(), Jin ZHANG(), Wanmeng ZHOU(), Lin LU()

College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China

Received:2019-09-16 Online:2020-03-28 Published:2020-03-28
Supported by:
国家自然科学基金(11572345);载人航天预先研究项目(010201)

摘要/Abstract

摘要：

针对返回近地空间站的月地转移轨道优化问题,提出一种基于改进多圆锥截线的高精度轨道设计方法。该类问题与再入大气月地轨道设计不同,需要考虑空间站轨道面约束。首先分析飞行任务过程,基于逆步长积分策略建立优化模型;然后根据地月位置关系,提出近月点窗口和轨道设计参数的初值估计方法;最后对多圆锥截线法进行改进,并与高精度轨道模型相结合,精确快速求解月地转移轨道。仿真算例验证提出的轨道优化策略具有较好的收敛特性和计算效率,并揭示了返回窗口、近月点出发域和速度增量的变化特性和规律。

关键词: 多圆锥截线, 月地返回轨道, 地心白道系, 近地空间站, 出发域

Abstract:

To optimize and design the return orbit from the Moon to the low Earth space station, an accurate and rapid approach based on the improved multi-conic method is proposed. It is different from Moon-to-Earth trajectories directly reentering the Earth atmosphere, where the coplanar constraints of the space station should be considered. Firstly, the flight process is analyzed and the optimization model is built with backward integration strategy. Then, based on the orbital geometric relationship in the cislunar space, an estimation method is proposed to determine the initial value of the perilune window and other orbital parameters. The improved multi-conic model is combined with the high-fidelity model and the transfer orbit is optimized rapidly and accurately with a cascade searching strategy. Simulation results show that the proposed solution strategy is effective and has good convergence. The fundamental patterns of the transfer window, perilune window and velocity increment are also revealed.

Key words: multi-conic method, Moon-to-Earth return orbit, Earth-centered Earth-to-Moon plane coordinate, low Earth space station, departure domain

中图分类号:

V412.4

杨路易, 李海阳, 张进, 周晚萌, 陆林. 基于改进多圆锥截线的月地返回轨道快速设计方法[J]. 系统工程与电子技术, 2020, 42(4): 896-903.

Luyi YANG, Haiyang LI, Jin ZHANG, Wanmeng ZHOU, Lin LU. Fast Moon-to-Earth return orbit design based on improved multi-conic method[J]. Systems Engineering and Electronics, 2020, 42(4): 896-903.

图/表 13

图1

图2

图3

图4

表1

表2

图5

图6

表3

图7

图8

图9

图10

参考文献 31

1	WU W R , LI C L , ZUO W , et al. Lunar farside to be explored by Chang'e-4[J]. Nature Geoscience, 2019, 12 (4): 222- 223.
2	ZHENG Y C , OUYANG Z Y , LI C L , et al. China's lunar exploration program: presemt and future[J]. Planetary and space Science, 2008, 56 (7): 881- 886. doi: 10.1016/j.pss.2008.01.002
3	LI J Y , GONG S P , WANG X . Analytical design methods for determining Moon-to-Earth trajectories[J]. Aerospace Science and Technology, 2015, 40, 138- 149. doi: 10.1016/j.ast.2014.10.016
4	GAO Y F , WANG Z K , ZHANG Y L . Analytical design methods for transfer trajectories between the earth and the Lunar Orbital Station[J]. Astrophysics and Space Science, 2018, 363 (206): 1- 12.
5	SHEN H X , ZHOU J P , PENG Q B , et al. Point return orbit design and characteristics analysis for manned lunar mission[J]. Science China Technological Sciences, 2012, 55 (9): 2561- 2569. doi: 10.1007/s11431-012-4969-4
6	陆林, 杨路易, 李海阳, 等. 载人飞船月地返回轨道优化设计与特性分析[J]. 系统工程与电子技术, 2019, 41 (12): 2842- 2848.
	LU L , YANG L Y , LI H Y , et al. Optimal design and characteristics analysis of the Moon-Earth return trajectory for manned spacecraft[J]. Systems Engineering and Electronics, 2019, 41 (12): 2842- 2848.
7	FENG F , ZHANG Y S . Application and analysis of an improved multi-conic method in trajectory design of the lunar south pole return mission[J]. Journal of Aerospace Engineering, 2018, 232 (6): 1063- 1076.
8	OCAMPO C A , SAUDEMONT R R . Initial trajectory model for a multi-maneuver moon-to-earth abort sequence[J]. Journal of Guidance, Control and Dynamics, 2010, 33 (4): 1184- 1194. doi: 10.2514/1.46955
9	WHITLEY R J , OCAMPO C A , WILLIAMS J . Performance of an autonomous multi-maneuver algorithm for lunar trans-earth injection[J]. Journal of Spacecraft and Rockets, 2012, 49 (1): 165- 174. doi: 10.2514/1.52710
10	JONES D R , OCAMPO C A . Optimization of impulsive trajectories from a circular orbit to an excess velocity vector[J]. Journal of Guidance, Control and Dynamics, 2012, 35 (1): 234- 244.
11	SHEN H X , CASALINO L . High-accurcy optimal finite-thrust trajectories for Moon escape[J]. Acta Astronautica, 2017, 131, 102- 109. doi: 10.1016/j.actaastro.2016.11.028
12	郑爱武, 周建平. 直接再入大气的月地返回窗口搜索策略[J]. 航空学报, 2014, 35 (8): 2243- 2250.
	ZHENG A W , ZHOU J P . A search strategy of back windows for moon-to-earth trajectories directly returning to the earth[J]. Acta Aeronautica Et Astronautica Sinica, 2014, 35 (8): 2243- 2250.
13	张磊, 于登云, 张熇. 月地转移轨道快速设计与特性分析[J]. 中国空间科学技术, 2011, 31 (3): 62- 70. doi: 10.3780/j.issn.1000-758X.2011.03.010
	ZHANG L , YU D Y , ZHANG H . Preliminary Design and characteristic analysis of moon-to-earth transfer trajectories[J]. Chinese Space Science and Technology, 2011, 31 (3): 62- 70. doi: 10.3780/j.issn.1000-758X.2011.03.010
14	贺波勇, 李海阳, 沈红新, 等. 载人登月着陆窗口与定点返回轨道耦合设计[J]. 国防科技大学学报, 2017, 39 (1): 11- 16.
	HE B Y , LI H Y , SHEN H X , et al. Coupling design of landing window and point return orbit for manned lunar landing mission[J]. Journal of National University of Defense and Technology, 2017, 39 (1): 11- 16.
15	CHUNG M K, WEINSTEIN S. Trajectory design of lunar south pole-aitken Basin sample return mission[C]//Proc.of the AIAA/AAS Astrodynamics Specialist Conference and Exhibit, 2004: 4739-4748.
16	EGOROV V A . Certain problems of moon flight dynamics[J]. Doklady Akademii Nauk SSSR(N.S.), 1957, 113, 46- 49.
17	周文艳, 杨维廉. 月球探测器的转移轨道特性分析[J]. 空间科学学报, 2004, 24 (5): 354- 359. doi: 10.3969/j.issn.0254-6124.2004.05.006
	ZHOU W Y , YANG W L . Analysis of the characteristics of the transfer trajectory of lunar explorer[J]. Chinese Journal of Space Science, 2004, 24 (5): 354- 359. doi: 10.3969/j.issn.0254-6124.2004.05.006
18	WILSON S W. A pseudostate theory for the approximation of three-body trajectories[C]//Proc.of the AAS/AIAA Astrodynamics Conference, 1970: 70-1061.
19	BYRNES D V, HOOPER H L. A fast and accurate method of computing space flight trajectories[C]//Proc.of the AAS/AIAA Astro-dynamics Conference, 1970, 70-1062.
20	RAMANAN R V . Integrated algorithm for lunar transfer trajectories using a pseudostate technique[J]. Journal of Guidance, Control and Dynamics, 2002, 25 (5): 946- 952. doi: 10.2514/2.4968
21	ROBINSON S, GELLER D. A simple targeting procedure for lunar trans-earth injection[C]//Proc.of the AIAA Guidance, Navigation and Contorl Conference, 2009: 6107.
22	LUO Q Q , YIN J F , HAN C . Design of earth-moon free-return trajectories[J]. Journal of Guidance, Control and Dynamics, 2012, 36 (1): 263- 271.
23	ZHOU W M , LI H Y , HE B Y , et al. Fixed-thrust earth-moon free return orbit design based on a hybrid multi-conic method of pseudo-perilune parameters[J]. Acta Astronautica, 2019, 160, 365- 377. doi: 10.1016/j.actaastro.2019.04.034
24	BAO C C , LI J Y , BAOYIN H X . Two-segment lunar free-return trajectories design using the pseudostate theory[J]. Advances in Space Research, 2018, 61 (1): 97- 110. doi: 10.1016/j.asr.2017.09.026
25	MURTAZIN R. Space transportation system of a new generation for the lunar space exploration program[C]//Proc.of the 67th International Astronautical Congress (IAC), 2016: IAC-16.D2.4.7.x32426.
26	彭祺擘.基于空间站支持的载人登月方案研究[D].长沙:国防科学技术大学, 2007.
	PENG Q B. Study on the scheme of manned lunar-landing mission supported by space station[D]. Changsha: National University of Defense Technology, 2007.
27	彭坤, 杨雷. 利用地月间空间站的载人登月飞行模式分析[J]. 宇航学报, 2018, 39 (5): 471- 481.
	PENG K , YANG L . Analysis on human lunar exploration flight modes via cislunar space station[J]. Journal of Astronautics, 2018, 39 (5): 471- 481.
28	LU P , CERIMELE C J , TIGGES M A , et al. Optimal aerocapture guidance[J]. Journal of Guidance, Control and Dynamics, 2015, 38 (4): 553- 565. doi: 10.2514/1.G000713
29	AI Y H , CUI H T , ZHENG Y Y . Identifying method of entry and exit conditions for aerocapture with near minimum fuel consumption[J]. Aerospace Science and Technology, 2016, 58, 582- 593. doi: 10.1016/j.ast.2016.09.018
30	CHEN Z L , WANG Z K , ZHANG Y L . Analysis and optimization of lunar exploration architecture based on reusable human spacecraft[J]. Journal of Spacecraft and Rockets, 2018, 56 (3): 910- 918.
31	GRISHKO D A, LEONOV V V, AYRAPETYAN M A, et al. Preliminary evaluation of multiple atmospheric re-entries in Lunar return missions[C]//Proc.of the IOP Conference Series: Materials Science and Engineering, 2018, 468(1): 012019.

运行高度 h_LEO/km	轨道倾角 i_LEO/(°)	升交点赤经 Ω_LEO/(°)	环月高度 h_LLO/km	环月倾角 i_LLO/(°)
343.0	42.4	60.0	200	90

	参数	多圆锥截线法	高精度模型	多圆锥截线法	高精度模型
设计参数	近地点时刻t_A	2028年4月17日 19:04:42.62	2028年4月17日 19:07:50.37	2028年5月2日 7:48:46.54	2028年5月2日 7:51:38.67
	近月点经度λ_prl	181.92	181.95	182.26	182.28
	近地脉冲v_A/(m/s)	3 120.73	3 122.36	3 113.42	3 115.04
	纬度幅角u_L/(°)	-6.71	-6.65	174.12	174.18
近月点参数	倾角i_LLO(°)	90.00	90.00	90.00	90.00
	升交点经度Ω_LLO(°)	140.58	140.60	147.45	147.48
	高度h_LLO/km	200.00	200.00	200.00	200.00
	纬度幅角u_LLO/(°)	236.98	236.94	50.67	50.62
	近月脉冲v_B/(m/s)	941.00	941.15	907.31	907.22
	计算时间/s	0.437	47.81	0.569	53.24

初值条件	生成轨道数	收敛数量	收敛率
近月点时刻+ 近地纬度幅角	1 000	1 000	100.0%
近月点时刻	1 000	875	87.5%
近地纬度幅角	1 000	219	21.9%
无初值	1 000	0	0.00%

基于改进多圆锥截线的月地返回轨道快速设计方法

Fast Moon-to-Earth return orbit design based on improved multi-conic method

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

图/表 13

参考文献 31

相关文章 1

编辑推荐

Metrics

本文评价