1、Remark: This Page can be completed under the help of a Chinese. Appendix 1: Template of an Academic Dissertation中图分类号：V475. 1 论 文 编 号 ：10006SY0415231 硕 士 学 位 论 文增压气路系统瞬变填充过程数值计算研究作 者 姓 名 X X X学 科 专 业 X X X X X X X X X指 导 教 师 X X X X X X培 养 院 系 宇航学院 Numerical Analysis of Transient Priming Process in
2、Pressurization Gas Pipeline SystemA Dissertation Submitted for the Degree of MasterCandidate: X X XSupervisor: X X X X XSchool of AstronauticsBeihang University, Beijing, ChinaRemark: This Page can be completed under the help of a Chinese.中图分类号：V475. 1 论 文 编 号 ：10006SY0415231 硕 士 学 位 论 文增压气路系统瞬变填充过程
3、数值计算研究作者姓名 XXX 申请学位级别 工学硕士指导教师姓名 XXX 职 称 教 授学科专业 航空宇航推进理论与工程 研究方向 XXXXX 学习时间自 2004 年 9 月 10 日 起至 2007 年 3 月 11 日止论文提交日期 2007 年 3 月 1 日 论文答辩日期 2007 年 3 月 11 日学位授予单位 北京航空航天大学 学位授予日期 年 月 日Remark: This Page can be completed under the help of a Chinese.关于学位论文的独创性声明本人郑重声明：所呈交的论文是本人在指导教师指导下独立进行研究工作所取得的成果，论
4、文中有关资料和数据是实事求是的。尽我所知，除文中已经加以标注和致谢外，本论文不包含其他人已经发表或撰写的研究成果，也不包含本人或他人为获得北京航空航天大学或其它教育机构的学位或学历证书而使用过的材料。与我一同工作的同志对研究所做的任何贡献均已在论文中作出了明确的说明。若有不实之处，本人愿意承担相关法律责任。学位论文作者签名： 日期： 年 月 日学位论文使用授权书本人完全同意北京航空航天大学有权使用本学位论文（包括但不限于其印刷版和电子版） ，使用方式包括但不限于：保留学位论文，按规定向国家有关部门（机构）送交学位论文，以学术交流为目的赠送和交换学位论文，允许学位论文被查阅、借阅和复印，将学位论
5、文的全部或部分内容编入有关数据库进行检索，采用影印、缩印或其他复制手段保存学位论文。保密学位论文在解密后的使用授权同上。学位论文作者签名： 日期： 年 月 日指导教师签名： 日期： 年 月 日i摘 要运载火箭增压输送系统是火箭推进系统的重要组成部分。常温氦气增压是液体火箭发动机推进剂贮箱增压的重要手段之一。增压系统的正常工作保证了推进剂的稳定供应以及发动机的正常运行。但是在高压氦气高速瞬变填充管路的过程中，由于高压高速氦气的非定常流动，极易产生压力的不稳定，作用在管道上，引发管道和各种管路元件的巨大振动，从而对系统产生极强的破坏作用，使增压不能达到预期效果，甚至导致增压系统失效。因此对高压气体
6、与管路振动过程的研究具有非常重要的意义。本论文通过对国内外同行管路系统研究成果的分析，以及对管路系统气体瞬变填充过程建模方法和气体动力学数值计算方法的深入研究和比较，以拉格朗日坐标下的一维非定常气体动力学方程组为基础，针对运载火箭一个典型增压气路系统及其系统组件，建立了典型气路系统高压氦气高速瞬变填充管路的流动过程的数学模型。并利用本论文的模型，采用完全守恒型差分格式的数值计算方法，用 FORTRAN 计算机语言编制了数值计算程序对该管路系统的非定常气动过程进行了数值计算，对不同算例的计算结果进行了分析和比较。结果表明，本论文建立的数学模型及数值计算方法较好地描述了增压气路系统的瞬变填充过程，
7、为分析运载火箭增压气路系统及其系统中的管路和减压器等组件的动态特性提供了重要的理论参考。为解决运载火箭增压气路系统中出现的管路振动问题，为后续研制过程中解决类似问题打下了基础。关键词：增压系统，数值计算，动力学模型，拉格朗日坐标iiAbstractPressurization system is very important in a flight vehicle propulsion system. Using the normal temperature gaseous helium to pressurize is one of the important means in propel
8、lant tank pressurization system of liquid propellant rocket engine. The regular operation of pressurization system ensures propellant supplying steadily and the engine operating normally. But in the fast and transient priming process of high-pressure gaseous helium, the unsteady gas flow is likely t
9、o cause unsteady pressue, consequently brings on violent vibrations of the whole gas pipeline system, which can seriously destroy the structure of the system and make the pressurization system invalid. Therefore the study on the transient priming process of high-pressure gaseous helium in pressurizi
10、ng gas pipeline system of a launch vehicle is significant.This dissertation focused on a typical pressurization gas pipeline system of a launch vehicle. On the basis of conservative equations of continuous gaseous media, one-dimensional unsteady gas-dynamic equations in Lagrangian form were derived
11、to describe compressible transient gas pipe flow, and dynamic equations of components including gas bottle, pressure reductor, orifice, and tee joint of the system were established. These components were considered as poits in the system. Accordingly a total dynamic mathematical model of a pressuriz
12、ation gas pipeline system was established. For this model, Lagrangian mass grids were established in the pipeline system. One-dimensional unsteady gas-dynamic equations in Lagrangian form of pipe flow were calculated in the fully conservative finite difference scheme, and Classical Runge-Kutta metho
13、d was used to calculate the dynamic equations of other components of this system. Based on the mathematical model and numerical calculation methods, a numerical calculation program was implemented using FORTRAN computer language, which could be used to calculate the fast and transient pipeline primi
14、ng process of high-pressure helium in the typical gas pipeline system of a launch vehicle. In this dissertation a typical transient priming process of the gas pipeline system was simulated with this program.The calculated results show that the mathematical model and numerial calculation iiimethods e
15、stablished in this thesis preferably described the fast and transient dynamic process of this system and provide a theoretical basis to analyze dynamic characteristics of the components such as pipelines and pressure reductor of pressurization gas pipeline system of a launch vehicle. These work make
16、s a foundation for further studies on vibration of pressurization gas pipeline system and other relevant problems. Key words: Pressurization system, Numerical calculation, Dynamic model, Lagrange coordinatesivContents1 Introduction 11.1 Background11.2 Research Status21.2.1 Oscillation 21.2.2 Dynamic
17、 characteristics .21.3 Dissertations Structure .22 Basic Theory .33 Mathematical Model 54 Program.75 Examples and Results 9Conclusion .11References13Research Fruits .15Acknowledgements .16BUAA Academic Dissertation for Masters Degree11 Introduction1.1 BackgroundPressurization system is very importan
18、t in a flight vehicle propulsion system. Using the normal temperature gaseous helium to pressurize is one of the important means in propellant tank pressurization system of liquid propellant rocket engine. The regular operation of pressurization system ensures propellant supplying steadily and the e
19、ngine operating normally. But in the fast and transient priming process of high-pressure gaseous helium, the unsteady gas flow is likely to cause unsteady pressue, consequently brings on violent vibrations of the whole gas pipeline system, which can seriously destroy the structure of the system and
20、make the pressurization system invalid. Therefore the study on the transient priming process of high-pressure gaseous helium in pressurizing gas pipeline system of a launch vehicle is significant.Figure 1 Pressurization System SketchTable 1 ParametersNo. Parameter Unite Value Remark氦气气瓶1 Pressure MP
21、a 232 Temperature K 288.15Introduction21.2 Research StatusPressurization system is very important in a flight vehicle propulsion system. Using the normal temperature gaseous helium to pressurize is one of the important means in propellant tank pressurization system of liquid propellant rocket engine
22、. 1.2.1 OscillationPressurization system is very important in a flight vehicle propulsion system. Using the normal temperature gaseous helium to pressurize is one of the important means in propellant tank pressurization system of liquid propellant rocket engine. 1.2.2 Dynamic characteristicsPressuri
23、zation system is very important in a flight vehicle propulsion system. Using the normal temperature gaseous helium to pressurize is one of the important means in propellant tank pressurization system of liquid propellant rocket engine. 1.3 Dissertations StructureBUAA Academic Dissertation for Master
24、s Degree32 Basic TheoryBUAA Academic Dissertation for Masters Degree53 Mathematical Model BUAA Academic Dissertation for Masters Degree74 ProgramBUAA Academic Dissertation for Masters Degree95 Examples and ResultsBUAA Academic Dissertation for Masters Degree11ConclusionThe calculated results show th
25、at the mathematical model and numerial calculation methods established in this thesis preferably described the fast and transient dynamic process of this system and provide a theoretical basis to analyze dynamic characteristics of the components such as pipelines and pressure reductor of pressurizat
26、ion gas pipeline system of a launch vehicle. These work makes a foundation for further studies on vibration of pressurization gas pipeline system and other relevant problems. BUAA Academic Dissertation for Masters Degree13References1 Ozgokmen T. M., Johns W. E., Peters H., et al. Turbulent Mixing in
27、 the Red Sea Outflow Plume from a High-Resoluting Nonhydrostatic ModelJ. Jounal of Physical Oceangraphy, 2003, V33(8): 1846-1869 2 Cai Yigang. Fluid Pipeline DynamicsM. Zhejiang: Zhengjiang University Press, 19903 LZHANG, ASTIJSSELING，AEVARDY. FSI Analysis of Lquid-filled PipesJ. Journal of Sound an
28、d Vibration，1999，224(1): 69-994 Ryuichi Sekita, Minoru Matsuda, Ryou NakamuraPressure Oscillation Analysis of the Pressure Regulator for the H-IIA Propulsion System RAIAA ，2003-46005 Mao Xia, et al Analysis of Affective Characteristics and Evaluation of Harmonious Feeling of Image Based on 1/f Fluct
29、uation TheoryAInternational Conference on Industrial & Engineering Applications of Artificial Intelligence & Expert Systems (IEA/AIE ) CAustralia Springer Publishing House,2002：17-196 Perry WStout，SAntony SnellMultipl On-Off Solenoid Valve Control for a Launch Vehicle Propellant Tank Pressurization
30、SystemJAIAA, 99-4085: 798-8047 Kimberly Holt，Alok Majumdar, Todd Steadman, et alNumerical Modeling and Test Data Comparison of Propulsion Test Article Helium Pressurization SystemR. AIAA, 2000-37198 Alok Majumdar，John WBailey，Paul Schallhorn，et alA Generalized Fluid System Simulation Program to Mode
31、l Flow Distribution in Fluid NetworksRAIAA 98-3682BUAA Academic Dissertation for Masters Degree15Research Outcomes1 Mao Xia, et al Analysis of Affective Characteristics and Evaluation of Harmonious Feeling of Image Based on 1/f Fluctuation TheoryAInternational Conference on Industrial & Engineering
32、Applications of Artificial Intelligence & Expert Systems (IEA/AIE ) CAustralia Springer Publishing House,2002：17-19BUAA Academic Dissertation for Masters Degree17AcknowledgementsMy deepest gratitude goes first and foremost to Professor aaa , my supervisor, for her constant encouragement and guidance
33、. She has walked me through all the stages of the writing of this thesis. Without her consistent and illuminating instruction, this thesis could not have reached its present form. Second, I would like to express my heartfelt gratitude to Professor aaa, who led me into the world of translation. I am
34、also greatly indebted to the professors and teachers at the Department of English: Professor dddd, Professor ssss, who have instructed and helped me a lot in the past two years. Last my thanks would go to my beloved family for their loving considerations and great confidence in me all through these years. I also owe my sincere gratitude to my friends and my fellow classmates who gave me their help and time in listening to me and helping me work out my problems during the difficult course of the thesis.
