低温推进剂贮箱增压系统分布参数数值仿真(Ⅰ)贮箱的有限体积模型

陈阳; 高芳; 张振鹏; 杨思锋

低温推进剂贮箱增压系统分布参数数值仿真(Ⅰ)贮箱的有限体积模型

1.
北京航空航天大学宇航学院, 北京 100083
2.
北京航天试验技术研究所, 北京 100074

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出版历程
- 收稿日期: 2007-01-15
- 修回日期: 2007-05-15
- 刊出日期: 2008-02-28

Distributed parameter numerical simulation for the transients of cryogenic propellant tank pressurization system(Ⅰ)Finite volume model of tank

1.
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Beijing Institute of Aerospace Testing Technology, Beijing 100074, China

摘要

摘要: 从准一维可压缩瞬变管流的有限体积模型出发,通过数值拓展和集成建立了一种考虑流体与箱壁传热的低温推进剂贮箱分布参数模型.流场采用一维交错网格的有限体积模型,可考虑变物性、轴向热传导、重力场、壁面传热影响;壁面温度场采用圆柱坐标系下的轴对称二维有限体积模型,可处理对流换热和辐射换热两种边界情况,可处理具有包覆层或真空夹层结构的变物性管壁传热.模型全面考虑了贮箱内的分布参数效应,适用于贮箱增压计算领域.
- 航空、航天推进系统 /
- 低温推进剂贮箱 /
- 准一维瞬变管流 /
- 二维瞬变传热 /
- 有限体积方法 /
- 数值仿真
Abstract: Based on the finite volume model of quasi one-dimensional compressible transient pipe flow,a distributed parameter numerical model of cryogenic propellant tank was established by numerical development and integration in which the heat transfer between fluid and tank wall was considered.Two kinds of finite volume grids,which are interlaced in discrete space,were employed to establish the flow field model which can consider actions derived from variable fluid properties,axial heat conductivity,gravity and wall heat transfer.Two-dimensional finite control volume grids in axisymmetric cylindrical coordinates were employed to establish the temperature field model which could deal with two boundary heat transfer conditions including convection and radiation.Variable thermophysical properties of wall material and multilayer or vacuum sandwich structure of tank wall were also considered.The model comprehensively describes the distributed parameter effect in tank and is valuable in tank pressurization simulation field.
- aerospace propulsion system /
- cryogenic propellant tank /
- quasi one-dimensional transient pipe flow /
- two-dimensional transient heat transfer /
- finite volume method /
- numerical simulation

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参考文献(12)

[1]	Van Dresar N T.Pressurization of cryogens:a review of current technology and its applicability to low-gravity conditions[R].AIAA92-3061,1992.
[2]	Van Dresar N T.Prediction of pressurant mass requirements for axisymmetric liquid hydrogen tanks[R].AIAA95-2964,1995.
[3]	Zilliac G,Karabeyoglu M A.Modeling of propellant tank pressurization[R].AIAA2005-3549,2005.
[4]	张超,鲁雪生,田丽亭.火箭低温液体推进剂增压系统数学模型[J].低温与超导,2005,33(2):35-38.ZHANG Chao,LU Xuesheng,TIAN Liting.The numerical model of rocket cryogenic liquid propellant pressurization system[J].Cryogenics and Superconductivity,2005,32(2):35-38.
[5]	Majumdar A,Steadman T.Numerical modeling of pressurization of a propellant tank[R].AIAA99-0879,1999.
[6]	Tarafder A,Sarangi S.CRESP-LP:a dynamic simulator for liquid-propellant rocket engines[R].AIAA2000-3768,2000.
[7]	Peukert M,Simon R.ATVSim the ATV propulsion system simulation software[R].AIAA2001-3828,2001.
[8]	Cullimore B A,Beer C M,Johnson D A.Propulsion applications of the NASA standard general purpose thermohydraulic analyzer[R].AIAA2000-3723,2000.
[9]	陈阳.液体火箭发动机试验台气路系统通用模块化建模与仿真研究[D].北京:北京航空航天大学,2006.CHEN Yang.Study on generalized modularization modeling and simulation for liquid propellant rocket engine testbed gas systems[D].Beijing:Beijing University of Aeronautics and Astronautics,2006.
[10]	陈阳,高芳,张振鹏,等.准一维可压缩瞬变管流的有限体积模型(Ⅰ)流场的有限体积模型[J].航空动力学报,2008,23(2):311-316.CHEN Yang,GAO Fang,ZHANG Zhenpeng,et al.Finite volume model for quasi one-dimensional compressible transient pipe flow(Ⅰ)Finite volume model of flow field[J].Journal of Aerospace Power,2008,23(2):311-316.
[11]	陈阳,高芳,张振鹏,等.准一维可压缩瞬变管流的有限体积模型(Ⅱ)管壁温度场的有限体积模型[J].航空动力学报,2008,23(2):317-322.CHEN Yang,GAO Fang,ZHANG Zhenpeng,et al.Finite volume model for quasi one-dimensional compressible transient pipe flow(Ⅱ)Finite volume model of temperature field[J].Journal of Aerospace Power,2008,23(2):317-322.
[12]	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.