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Topic:The technology of new generation medium-lift launch vehicle
Topic:The technology of new generation medium-lift launch vehicle
Integrated Design Technology of Electrical System for the Long March 8 Launch Vehicle
- ZHOU Tao1, XU Yang2, HU Haifeng1, ZHANG Siyan2, ZHANG Huanxin1
Author information
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1. Beijing Aerospace Automatic Control Institute,Beijing 100854,China;
2. Beijing Institute of Space System Engineering,Beijing 100076,China
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History
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Received |
Revised |
Published |
01 Feb 2020 |
30 Apr 2020 |
20 Feb 2021 |
Issue Date |
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20 Feb 2021 |
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Integrated design is the main development trend of the spacecraft electrical system. The development status of electrical system in the new generation launch vehicle at home and abroad is reviewed, and the integrated architecture of electrical system based on the redundant system bus and integrated electronic architecture is put forward for the new generation medium Long March 8 (CZ-8) launch vehicle. The integrated design technology of electrical system is introduced from the aspects of system integration, power supply integration, software integration, test integration and telemetry integration. The integrated design technology will be used for the integration of system functions, and also for the breakthrough of the electrical system from traditional sub-system development to cross-system integration. Therefore, the integrated design technology of the electrical system can be used to simplify the test launch process and improve the launch capability, meeting the needs of a new generation of medium launch vehicles with low cost, high reliability, and fast launch.
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References
[1] 宋征宇. 信息集成在航天运输控制系统中的应用研究[J]. 宇航学报,2015,36(4):365-374
SONG Z Y. Application study of information integration in aerospace transportation control system[J]. Journal of Astronautics,2015,36(4):365-374
[2] 秦旭东,龙乐豪,容易.我国航天运输系统成就与展望[J].深空探测学报(中英文), 2016, 3(4): 315-322.
QIN X D, LONG L H,RONG Y.The achievement and future of China space transportation system[J].Journal of Deep Space Exploration, 2016,3(4):315-322.
[3] 宋征宇. 考虑成本效率的航天系统研制[J]. 航天控制,2015,33(6):3-11
SONG Z Y. The study on the development of cost-effective launch vehicle[J]. Navigation and Control,2015,33(6):3-11
[4] 杨军,蓝鲲. 运载火箭信息化集成设计的基本途径设想[J]. 宇航学报,2007,28(3):682-684
YANG J,LAN K. A conception of primary approach to integrated information design[J]. Journal of Astronautics,2007,28(3):682-684
[5] 宋征宇. 新一代运载火箭电气系统体系架构的研究[J]. 载人航天,2016,22(3):317-322
SONG Z Y. Research on avionics system configuration of next generation launch vehicle[J]. Manned Spaceflight,2016,22(3):317-322
[6] 胡海峰,吕新广,宋征宇. 长征系列运载火箭控制系统划代研究[J]. 航天控制,2016,34(6):15-25
HU H F,LYU G,SONG Z Y. Research on GNC system generation of Long March launch vehicles[J]. Aerospace Control,2016,34(6):15-25
[7] 胡海峰,宋征宇,孙海峰. 新型中型运载火箭控制系统架构及发展[J]. 导弹与航天运载技术,2019(2):49-53
HU H F,SONG Z Y,SUN H F. Review of avionics architecture of new medium launch vehicle and development[J]. Missiles and Space Vehicles,2019(2):49-53
[8] NOLA C L,BLUE L. NASA Ares I crew launch vehicle upper stage avionics and software overview[EB/OL]. (2009)[2020-02-01]. http://www.ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090020393_2008048231.pdf.
[9] TILLER B K. Ares first stage element status[EB/OL]. (2009) [2020-02-01]. http://Ntrs.nasa.gov/archive/nasa/casi.Ntrs.nasa.gov/20090037677.pdf.
[10] MAY T. Space launch system:SLS at critical design review[EB/OL]. (2015)[2020-02-01]. http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20150019522.pdf.
[11] 康开华,丁文华. 首枚猎鹰-9运载火箭升空[J]. 国际太空,2010(6):21-26
[12] SpaceX. Falcon 9 launch vehicle payload user’s guide[M]. USA: Space Exploration Technologies Corporation,2015.
[13] MONCHAUX D,GAST P,SANGARE J. Avionic-X:a demonstrator for the next generation launcher avionics[C]//Embedded Real Time Software And Systems. ERTS2. Toulouse,Feance:[s. n.],2012.
[14] JAXA. Epsilon launch vehicle[EB/OL]. (2013)[2020-02-01]. http://global.jaxa.jp/projects/rockets/epsilon/index.html.
[15] MORITA Y,IMOTO T,TOKUDOME S,et al. A year to launch:Japan’s epsilon launcher and its evolution[C]// 63rd International Astronautical Congress. Naples,Italy:[s. n. ],2012.
[16] 高松涛. 运载火箭电气系统一体化测试方案构想[J]. 导弹与航天运载技术,2001(4):1-5
GAO S T. Integrated test notion for electrical systems of launch vehicle[J]. Missiles and Space Vehicles,2001(4):1-5
[17] 刘亮亮,蒋彭龙. 系统集成是航天控制系统的发展方向[J]. 航天标准化,2011(3):6-9
[18] GU Q F,WANG G Q,HE Y Z. Dynamic reconfiguration mechanism for distributed integrated modular avionics system[C]//AIAA Aviation Forum. Dallas:AIAA,2015.
[19] CIUCCI A,PILCHEN,RESTA P D,et al. Ariane 6 new concept,new governance status and perspectives[C]//66th International Astronautical Congress. Jerusalem,Israel:[s. n. ],2015.
[20] United Launch Alliance. Atlas V launch services user’s guide[R]. USA: United Launch Alliance,2010.
[21] GEOHAGAN K,LEGGETT T,OLIVER T E,et al. 6DOF testing of the SLS Inertial navigation unit[C]//41st Annual Guidance and Control Conference. Breckenridge,CO,United States:[s. n. ],2018.
[22] SHAUN P,KEN K. SLS flight software agile development process[C]//IEEE Standard 1012 System,Software and Hardware Verification and Validation Working Group Meeting. United States: IEEE, 2015.