|Table of Contents|

Summary of virtual test and simulation technology application in LRE field(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2021年04期
Page:
87-95
Research Field:
测控与试验
Publishing date:

Info

Title:
Summary of virtual test and simulation technology application in LRE field
Author(s):
YANG SifengDUAN NaZHANG DengpanZHU ZihuanLI Bin
(Beijing Institute of Aerospace Testing Technology,Beijing 100074,China)
Keywords:
simulation validation virtual test liquid rocket engine(LRE)
PACS:
V433
DOI:
-
Abstract:
This article describes the fundamental theory of virtual test and simulation verification technology,including the application cases of Jet Laboratory(US),Marshall Space Flight Center(US),Kennedy Space Center(US),Green Research Center(US),Russian Science Test Center,Stennis Research Center(US),DLR Center(Germany),Kakuda Space Propulsion Center(Japan),French Aerospace Agency and other liquid rocket engine development and test institutions in the field of virtual test and simulation research.Their application results are promoted and applied in the form of mature products,and the application products of China in this field are compared.Finally,the development trend of this technology,test bed application and related research suggestions are reviewed.Through the summary and analysis,it can be seen that the simulation work of foreign liquid rocket engines has wide coverage and high credibility,and the whole working process from the system level to the component level can be accurately simulated in real time.All models have been verified and corrected by real test runs or flight data, providing technical references for the implementation and application of virtual test and simulation platforms in the field of engine testing.

References:

[1] JAMES M L,BAROTH E,MELLINGER L,et al.Integrated virtual test bed for ivhm systems on 2nd generation RLV[C]//2003 IEEE Aerospace Conference Proceedings Big Sky.MT:IEEE,2003.
[2] RABELO L.The virtual test bed project[Z].2004.
[3] FOLLETT R,TAYLOR R,NUNEZ S.Liquid rocket propulsion dynamic flow modeling using the ROCETS engineering modules in the EASY5x environment[C]//29th Joint Propulsion Conference and Exhibit.Monterey,CA.Reston,Virginia:AIAA,1993.
[4] MAUL W,CHICATELLI A,FULTON C,et al.Addressing the real-world challenges in the development of propulsion IVHM technology experiment(PITEX)[C]//AIAA 1st Intelligent Systems Technical Conference.Chicago,Illinois.Reston,Virginia:AIAA,2004
[5] LYTLE K,FOLLEN J,NAIMAN G,et al.Numerical Propulsion System Simulation(NPSS)2000 industry review[Z].NASA Glenn Research Center,2001.
[6] Fernando Figueroa and Randy Holland.ISHM implementation for constellation systems[R].AIAA 2006-4410.
[7] SASSNICK H D,KRUELLE G.Numerical simulation of transients in feed systems for cryogenic rocket engines[C]//31st Joint Propulsion Conference and Exhibit.San Diego,CA.Reston,Virginia:AIAA,1995.
[8] YAMANISHI N,KIMURA T,TAKAHASHI M,et al.Transient analysis of the LE-7A rocket engine using the rocket engine dynamic simulator(REDS)[C]//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Fort Lauderdale,Florida.Reston,Virigina:AIAA,2004.
[9] ORDONNEAU G,ALBANO G,LEUDIERE V.CARINS:a new versatile and flexible tool for engine transient prediction development status[C]//6th International Symposium on Launcher Technologies.Munich,Germany:[s.n.],2005.
[10] CROWDER J.Multiple information agents for real-time,ISHM:Architectures for real-time warfighter support[R].AIAA 2010-3478.
[11] JOHN S,FERNANDO F,MARK S,et al.Anomaly detection toolkit for integrated systems health management(ISHM)[R].AIAA2010-3498.
[12] FIGUERO A F,MORRIS J,NICKLES D,et al.Intelligent sensors and components for on-board ISHM[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Sacramento,California.Reston,Virigina:AIAA,2006.
[13] PISANICH G,BAJWA A,SANDERFER D,et al.An abort failure detection,notification,& response system:overview of an ISHM development process[C]//2008 IEEE Aerospace Conference.Big Sky,MT:IEEE,2008.
[14] RUSSELL M J,LECAKES G D,MANDAYAM S,et al.The “intelligent” valve:a diagnostic framework for integrated system-health management of a rocket-engine test stand[J].IEEE Transactions on Instrumentation and Measurement,2011,60(4):1489-1497.
[15] FIGUEROA F,AGUILAR R.Test stand and J-2X engine end-to-end integrated system health management demonstration[C]//43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Cincinnati,OH.Reston,Virginia:AIAA,2007.
[16] FIGUEROA F,SCHMALZEL J,AGUILAR R,et al.Integrated system health management(ISHM)for test stand and J-2X engine:core implementation[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Hartford,CT.Reston,Virginia:AIAA,2008
[17] FERNANDO F.Integrated systems health management(ISHM)enabling intelligent systems[C]//NASA/ESA conference on Adaptive Hardware and Systems(AHS-2011).San Diego,California:NASA,2011.
[18] 王绪智,张宝珍.国外PHM 技术的发展动态及经验教训[J].测控技术.2010,29:216-219.
[19] 张宝珍.国外综合诊断、预测与健康管理技术的发展及应用[J].计算机测量与控制,2008,16(5):591-594.
[20] NASA Marshall Space Flight Center.Balanced flow metering and conditioning technology for fluid systems[Z].2006.
[21] GROSSE M.Effect of a diaphragm on performance and fuel regression of a laboratory scale hybrid rocket motor using nitrous oxide and paraffin[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Denver,Colorado:AIAA,2009.
[22] DENIEL A,VINEET A.Computational pluma modeling of conceptual ARES vehicle stage test[R].AIAA2006-3411.
[23] BALEPIN V.Concept of the third fluid cooled liquid rocket engine[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Sacramento,California:AIAA,2006.
[24] MATTHIJSSEN R.Ultrasonic flow meter for satellite propellant gauging and ground test facilities[R].AIAA 2008-4854.
[25] 谭永华.中国重型运载火箭动力系统研究[J].火箭推进,2011,37(1):1-6. TAN Y H.Research on power system of heavy launch vehicle in China[J].Journal of Rocket Propulsion,2011,37(1):1-6.
[26] JAMES M L,BAROTH E,MELLINGER L,et al.Integrated virtual test bed for ivhm systems on 2nd generation RLV[C]//2003 IEEE Aerospace Conference Proceedings(Cat.No.03TH8652).Big Sky,MT:IEEE,2003.
[27] 闫少光,门昱,周彬文,等.卫星真空热试验数据库的设计与实现[J].航天器环境工程,2006,23(4):201-204.
[28] 张育林,刘昆,程谋森.液体火箭发动机动力学理论与应用[M].北京:科学出版社,2005.
[29] 李家文,张黎辉,张振鹏.液体火箭发动机数值模拟的计算模型建立方法[J].推进技术,2002,23(5):363-365.
[30] 高芳,陈阳,张振鹏,等.液体火箭发动机实验台液路系统工作过程仿真[J].航空动力学报,2006,21(2):417-420.
[31] 刘昆,张育林.液体推进系统充填过程的有限元状态变量模型[J].推进技术,2001,22(1):19-21.
[32] 黄卫东,朱恒伟,王克昌,等.液体火箭发动机静态仿真通用模块化方法[J].航空动力学报,1998,13(1):53
[33] 杨雪,张振鹏,杨思锋.基于AHP的液体火箭发动机地面试验监测参数的选取方法研究[J].航空动力学报,2006,21(3):615-620.
[34] 刘杰.基于HLA飞行仿真系统框架的构建[D].济南:山东大学,2005.
[35] 黄柯棣.系统仿真技术[M].长沙:国防科学技术大学出版社,1998.
[36] 王国权.虚拟试验技术[M].北京:电子工业出版社,2004.
[37] 朱名铨,张树生.虚拟制造系统与实现[M].西安:西北工业大学出版社,2001.
[38] 何江华.计算机仿真导论[M].北京:科学出版社,2001.
[39] 冯润明,王国玉,黄柯棣.TENA及其与HLA的比较[J].系统工程与电子技术,2005,27(2):288-291.
[40] 齐欢,代建民,吴义明,等.HLA仿真与UML建模[M].北京:科学出版社,2004.
[41] JORGE B,AJKUMAR T.Intelligent launch and range operations virtual test bed(ILRO-VTB)[EB/OL].http://ic-www.are.nasa.gov/Publieations/Pdf/0489.Pdf,2006.
[42] 孙磊.Windows系列操作系统下的底层驱动技术在实时控制系统中的应用[D].西安:中国科学院研究生院,2007.
[43] 张奕.Windows2000 WDM驱动程序开发技术的研究[D].西安:西安电子科技大学,2001.
[44] 耶国栋.Windows下三类典型驱动程序的设计与实现[D].西安:西安电子科技大学,2005.
[45] 徐君.Windows2000 平台与下层工控机的信息交互[D].西安:西安电子科技大学,2005.
[46] 吴延林.仿真模型库系统的研究与实现[D].长沙:国防科学技术大学,2005.
[47] WHITTLE J,ARAUJO J.Scenario modelling with aspects[J].IEE Proceedings-Software,2004,151(4):157-171.
[48] 王军.遵循IEEE1516标准的对象模型开发工具研究与实现[D].长沙:国防科学技术大学,2004.
[49] 彭健,赵雯,章乐平,等.虚拟试验支撑框架VITA研究与实现[J].计算机测量与控制,2017,25(8):289-293.
[50] 刘昆,张育林,程谋森.液体火箭发动机系统瞬变过程模块化建模与仿真[J].推进技术,2003,24(5):401-405.

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Last Update: 1900-01-01