Research on agile space emergency launching mission planning simulation and verification method

doi:10.23919/JSEE.2023.000067

Journal of Systems Engineering and Electronics ›› 2023, Vol. 34 ›› Issue (5): 1267-1284.doi: 10.23919/JSEE.2023.000067

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Research on agile space emergency launching mission planning simulation and verification method

Feng WU¹^,*(), Xiuluo LIU¹(), Jia WANG¹(), Chao LI²(), Ying LIU¹(), Jianbin SU¹(), Ailiang ZHANG¹(), Min WANG¹()

¹ Beijing Institute of Tracking and Telecommunications Technology, Beijing 100094, China
² CASIC Space Engineering Development Co. Ltd., Beijing 100854, China

Received:2022-07-12 Online:2023-10-18 Published:2023-10-30
Contact: Feng WU E-mail:2904099828@qq.com;glenliu@263.net;kelexuebi2009@163.com;446591391@qq.com;fq_1982@126.com;sujianbin1983@163.com;zhangailiang1966@126.com;2548181884@qq.com
About author:
WU Feng was born in 1980. He received his bachelor ’s degree in applied mathematics from the Department of Mathematics, Huazhong University of Science and Technology, Wuhan, China in 2003. He received his master’s degree in applied mathematics from the Department of Mathematics in National University of Defense Technology, Changsha, China in 2005. He received his Ph.D. degree in computer science and technology from the Computer College in National University of Defense Technology, Changsha, China in 2009. From January 2010 to now, he is an assistant research fellow with Beijing Institute of Tracking and Telecommunications Technology and his main research direction is space launching informatization. His research interests include distributed computing software, computer simulation, scientific computation, and data visualization. E-mail: 2904099828@qq.com

LIU Xiuluo was born in 1974. He received his B.E., and Ph.D. degrees in control science and engineering from National University of Defense Technology, Changsha, China, in 1996, and 2001, respectively. From December 2002 to December 2004, he held a Postdoctoral Fellowship in the Training Simulation Center, National Defense University. He is currently an associate research fellow with Beijing Institute of Tracking and Telecommunications Technology. His research interests include system simulation and digital engineering in aerospace. E-mail: glenliu@263.net

WANG Jia was born in 1983. She received her B.E., and M.E. degrees in computer science and technology from National University of Defense Technology, Changsha, China, in 2004 and 2006, respectively. She is currently an assistant research fellow with Beijing Institute of Tracking and Telecommunications Technology. Her research interests include launch informatization and test evaluation. E-mail: kelexuebi2009@163.com

LI Chao was born in 1990. He received his Ph.D. degree in control science and engineering from the Department of Automation, Beijing Institute of Technology, Beijing, China, in 2019. He works as an intermediate engineer at CASIC Space Engineering Development Co. Ltd., Beijing, China. His research interest is space launching informatization. E-mail: 446591391@qq.com

LIU Ying was born in 1979. He received his bachelor’s degree from East China Jiaotong University in 2001 and master ’s degree from Beihang University in 2004. From April 2004 to now, he is an associate research fellow with Beijing Institute of Tracking and Telecommunications Technology. His research interests include carrier rocket entire design, test and launching. E-mail: fq_1982@126.com

SU Jianbin was born in 1983. He received his B.E., M.E., and Ph.D. degrees in control science and engineering from National University of Defense Technology, Changsha, China, in 2006, 2008, and 2013, respectively. He is currently an assistant research fellow with Beijing Institute of Tracking and Telecommunications Technology. His research interest is rapid launch in aerospace. E-mail: sujianbin1983@163.com

ZHANG Ailiang was born in 1966. In 1990 and 2014, he received his bachelor ’s degree from Wuhan University of Surveying and Mapping Technology and master ’s degree in engineering from Beijing Institute of Technology. He has been engaged in command and control of space launching and is now an associate researcher with Beijing Institute of Tracking and Telecommunications Technology. His research interests include space launch informatization and test evaluation. E-mail: zhangailiang1966@126.com

WANG Min was born in 1990. He received his B.E. degree from Chengdu University of Technology, Chengdu, China, in 2015. He is currently an assistant research fellow with Beijing Institute of Tracking and Telecommunications Technology. His research interest is space launching digitization. E-mail: 2548181884@qq.com

Abstract

Abstract:

Space emergency launching is to send a satellite into space by using a rapid responsive solid rocket in the bounded time to implement the emergency Earth observation mission. The key and difficult points mainly include the business process construction of launching mission planning, validation of the effectiveness of the launching scheme, etc. This paper proposes the agile space emergency launching mission planning simulation and verification method, which systematically constructs the overall technical framework of space emergency launching mission planning with multi-field area, multi-platform and multi-task parallel under the constraint of resource scheduling for the first time. It supports flexible reconstruction of mission planning processes such as launching target planning, trajectory planning, path planning, action planning and launching time analysis, and can realize on-demand assembly of operation links under different mission scenarios and different plan conditions, so as to quickly modify and generate launching schemes. It supports the fast solution of rocket trajectory data and the accurate analysis of multi-point salvo time window recheck and can realize the fast conflict resolution of launching missions in the dimensions of launching position and launching window sequence. It supports lightweight scenario design, modular flexible simulation, based on launching style, launching platform, launching rules, etc., can realize the independent mapping of mission planning results to two-dimensional and three-dimensional visual simulation models, so as to achieve a smooth connection between mission planning and simulation.

Key words: emergency launching, launching mission planning, launching process simulation, satellite orbit planning, rocket trajectory planning

Feng WU, Xiuluo LIU, Jia WANG, Chao LI, Ying LIU, Jianbin SU, Ailiang ZHANG, Min WANG. Research on agile space emergency launching mission planning simulation and verification method[J]. Journal of Systems Engineering and Electronics, 2023, 34(5): 1267-1284.

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References 37

1	ZHANG D C, FAN Z Z Research on mission planning and launching flow of solid rocket emergency launching. Modern Defence Technology, 2018, 46 (6): 122- 128.
2	CAI Y Z, HE S F, GU Z F, et al Mission planning of operationally responsive space for solid launching vehicle. Modern Defence Technology, 2021, 49 (1): 107- 115.
3	HU J X, HUANG H, YANG L P, et al A multi-objective optimization framework of constellation design for emergency observation. Advances in Space Research, 2021, 67 (1): 531- 545. doi: 10.1016/j.asr.2020.09.031
4	TOMER S, PINI G Low Earth orbit satellite constellation for regional positioning with prolonged coverage durations. Advances in Space Research, 2019, 63 (8): 2469- 2494. doi: 10.1016/j.asr.2019.01.010
5	ZHANG S Y, ZHU Z C, HU H Y, et al Research on task satellite selection method for space object detection leo constellation based on observation window projection analysis. Aerospace, 2021, 8 (6): 156. doi: 10.3390/aerospace8060156
6	WEN J, LIU X L, HE L Real-time online rescheduling for multiple agile satellites with emergent tasks. Journal of Systems Engineering and Electronics, 2021, 32 (6): 1407- 1420. doi: 10.23919/JSEE.2021.000120
7	Teledyne Brown Engineering Inc. EADSIM executive summary. http://www.eadsim .com/EADSIMExecSum.pdf.
8	Ternion Corporation. FLAMES modeling & simulation software by Ternion. http://www.ternion.com.
9	DANIEL T M. An overview of the joint warfare system (JWARS). Mclean: MITRE Corporation, 2000.
10	ANDY B, DAVID P. Multi-resolution modeling in the JTLS-JCATS federation. Mclean: MITRE Corporation, 2003.
11	SU Y T, HOU L, LI Y F Tactical maneuver model design and implementation on extensible simulation platform. Fire Control & Command Control, 2019, 44 (5): 125- 130.
12	XU L, LIN S Y, HLYNKA A W, et al Distributed simulation platforms and data passing tools for natural hazards engineering: reviews, limitations, and recommendations. International Journal of Disaster Risk Science, 2021, 12 (2): 617- 634.
13	GAO F, ZANG A, BI W H Weapon system operational effectiveness evaluation based on the belief rule-based system with interval data. Journal of Intelligent and Fuzzy Systems, 2020, 39 (5): 6687- 6701. doi: 10.3233/JIFS-190651
14	GU Y, HAN C, CHEN Y H, et al Mission replanning for multiple agile earth observation satellites based on cloud coverage forecasting. IEEE Journal of Selected Topics in Applied Earth Observations and Remote Sensing, 2022, 15, 594- 608. doi: 10.1109/JSTARS.2021.3135529
15	ZHUO H H, KAMBHAMPATI S Model-lite planning: cased-based vs. model-based approaches. Artificial Intelligence, 2017, 246, 1- 21.
16	HASLUM P, IVANKOVIC F, RAMIREZ M, et al Extending classical planning with state constraints: heuristics and search for optimal planning. Journal of Artificial Intelligence Research, 2018, 62, 373- 431. doi: 10.1613/jair.1.11213
17	SOLEYMANI M, FAKOOR M, BAKHTIARI M Optimal mission planning of the reconfiguration process of satellite constellations through orbital maneuvers: a novel technical framework. Advances in Space Research, 2019, 63 (10): 3369- 3384. doi: 10.1016/j.asr.2019.02.003
18	FAKOOR M, BAKHTIARI M, SOLEYMANI M Optimal design of the satellite constellation arrangement reconfiguration process. Advances in Space Research, 2016, 58 (3): 372- 386. doi: 10.1016/j.asr.2016.04.031
19	NIU C H, LI A J, HUANG X, et al. Research on global dynamic path planning method based on improved A* algorithm. Mathematical Problems in Engineering, 2021, 2021: 1−13.
20	LI H M, XIANG S W, JIA W S, et al Solving multiobjective game in multiconflict situation based on adaptive differential evolution algorithm with simulated annealing. Mathematical Problems in Engineering, 2021, 2021 (1): 1- 11.
21	WEI Z F, CHENG Y, GUO X X, et al Hybrid trajectory optimization method and tracking guidance for variable-sweep missiles. Mathematical Problems in Engineering, 2021, 2021, 1- 14.
22	MORGADO F M P, MARTA A C, GIL P S Multistage rocket preliminary design and trajectory optimization using a multidisciplinary approach. Structural and Multidisciplinary Optimization, 2022, 65 (7): 192. doi: 10.1007/s00158-022-03285-y
23	CAMPOS L, GIL P The two-point boundary-value problem for rocket trajectories. Aerospace, 2020, 7 (9): 131. doi: 10.3390/aerospace7090131
24	BORIS B, ALESSANDRO Z, GUIDO C, et al Convex approach to three-dimensional launch vehicle ascent trajectory optimization. Journal of Guidance, Control, and Dynamics, 2021, 44 (2): 1- 16.
25	DENG W, SHANG S F, CAI X, et al An improved differential evolution algorithm and its application in optimization problem. Soft Computing, 2021, 25 (7): 5277- 5298. doi: 10.1007/s00500-020-05527-x
26	VISHNU S N, ARAVIND V Ascent trajectory design and optimization of a two-stage throttleable liquid rocket. Advances in Space Research, 2022, 69 (12): 4358- 4375. doi: 10.1016/j.asr.2022.03.023
27	ZHU L H, WANG Y, WU Z Q, et al The intelligent trajectory optimization of multistage rocket with gauss pseudo-spectral method. Intelligent Automation & Soft Computing, 2022, 33 (1): 291- 303.
28	LORENZO F, ALESSANDRO Z, GUIDO C, et al Integrated optimization of first-stage SRM and ascent trajectory of multistage launch vehicles. Journal of Spacecraft and Rockets, 2021, 58 (4): 1- 12.
29	MAHJUB A, MAZLAN N M, ABDULLAH M Z, et al Design optimization of solid rocket propulsion: a survey of recent advancements. Journal of Spacecraft and Rockets, 2020, 57 (1): 3- 11. doi: 10.2514/1.A34594
30	BENEDIKTER B, ZAVOLI A, COLASURDO G, et al. Convex optimization of launch vehicle ascent trajectory with heat flux and splash-down constraints. Proc. of the AAS/AIAA Astrodynamics Specialist Conference, 2020: 1–20.
31	BAI X Z, CHEN L A rapid algorithm of space debris collision probability based on space compression and infinite series. Acta Mathematicae Applicatae Sinica, 2009, 32 (2): 336- 353.
32	BAI X Z, CHEN L, ZHANG Y, et al Survey on collision assessment and warning techniques for space object. Journal of Astronautics, 2013, 34 (8): 1027- 1039.
33	BAI X Z, CHEN L Explicit expression and influencing factor analysis of collision probability between space objects. Chinese Journal of Space Science, 2009, 29 (4): 422- 431. doi: 10.11728/cjss2009.04.422
34	RANA T EX-MAN component model for component-based software construction. Arabian Journal for Science and Engineering, 2020, 45, 2915- 2928. doi: 10.1007/s13369-019-04213-x
35	NICOLA R D, MAGGI A, SIFAKIS J The dream framework for dynamic reconfigurable architecture modelling: theory and applications. International Journal on Software Tools for Technology Transfer, 2020, 22 (4): 437- 455. doi: 10.1007/s10009-020-00555-2
36	REISIG W. Composition of component models-a key to construct big systems. Proc. of the 9th International Symposium on Leveraging Application of Formal Methods, 2020. DOI: 10.1007/978-3-030-61470-6_11.
37	DUAN J H, LIU Y F Two-dimensional launch window method to search for launch opportunities of interplanetary missions. Chinese Journal of Aeronautics, 2020, 33 (3): 965- 977. doi: 10.1016/j.cja.2019.12.010

Orbital height/km	SSO			LEO			Retrograde orbit			Summation
Orbital height/km	T-Q	S-Q	S-R/%	T-Q	S-Q	S-R/%	T-Q	S-Q	S-R/%	T-Q	S-Q	S-R/%
268	0	0	-	0	0	-	54	49	90.74	54	49	90.74
286	0	0	-	0	0	-	52	43	82.69	52	43	82.69
300	52	49	94.23	48	43	89.58	52	45	86.54	152	137	90.13
400	0	0	-	24	24	100	0	0	-	24	24	100
500	52	50	96.15	48	46	95.83	0	0	-	100	96	96
700	52	49	94.23	24	23	95.83	0	0	-	76	72	94.74
Summation	156	148	94.87	144	136	94.44	158	137	86.71	458	421	91.92

Orbital height/km	SSO/%	LEO/%	Retrograde orbit/%
268	0	0	13.51
286	0	0	24.32
300	8.11	13.51	18.92
400	0	0	0
500	5.41	5.41	0
700	8.11	2.70	0

Orbit parameter	Number
Orbit semi-major axis/km	6646.137
Trajectory inclination/(°)	139
Orbital eccentricity	0
Orbital plane number	4
Satellite number in each orbital plane	6
Phase factor	1

Satellite	Launching time window (UTC time)
Satellite	Launching area 1	Launching area 2	Launching area 3
The first orbital plane No.1-3 satellite	March 18, 2022 22:23:58.575−22:24:20.931	——	——
The first orbital plane No.4-6 satellite	——	March 18, 2022 00:32:55.090−00:32:57.466	——
The second orbital plane No.1-3 satellite	March 18, 2022 04:22:03.49−04:22:23.732	——	——
The second orbital plane No.4-6 satellite	——	March 18, 2022 06:28:44.850−06:28:55.940	——
The third orbital plane No.1-3 satellite	March 18, 2022 11:43:38.056−11:44:16.717	——	——
The third orbital plane No.4-6 satellite	——	March 18, 2022 12:24:38.860−12:24:50.151	——
The fourth orbital plane No.1-3 satellite	March 18, 2022 17:39:29.764−17:40:08.737	——	——
The fourth orbital plane No.4-6 satellite	——	——	March 18, 2022 14:05:58.264−14:06:15.460

Latitude coordinate/(°)	Average revisit time (hour, minute, second)	The max revisit time (hour, minute, second)
25.05	0:56:38	4:01:47
24.1386	1:07:31	3:47:47
23.1725	1:07:31	3:33:49
22.6306	0:58:01	3:33:49
22.6667	1:04:26	3:33:50

Research on agile space emergency launching mission planning simulation and verification method

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