[1]陈 军.固体火箭高温高压复杂燃气系统的黏性系数和导热系数计算[J].弹道学报,2020,32(01):55-63.[doi:10.12115/j.issn.1004-499X(2020)01-008]
 CHEN Jun.Calculation of Viscosity Coefficient and Thermal Conductivity ofHigh-temperature High-pressure Gas Mixture of Solid Rocket[J].Journal Of Ballistics,2020,32(01):55-63.[doi:10.12115/j.issn.1004-499X(2020)01-008]
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固体火箭高温高压复杂燃气系统的黏性系数和导热系数计算()
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《弹道学报》[ISSN:1004-499X/CN:32-1343/TJ]

卷:
32
期数:
2020年01期
页码:
55-63
栏目:
出版日期:
2020-03-31

文章信息/Info

Title:
Calculation of Viscosity Coefficient and Thermal Conductivity ofHigh-temperature High-pressure Gas Mixture of Solid Rocket
文章编号:
1004-499X(2020)01-0055-09
作者:
陈 军
南京理工大学 机械工程学院,江苏 南京 210094
Author(s):
CHEN Jun
School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China
关键词:
固体火箭 输运系数 黏性系数 导热系数 固体推进剂
Keywords:
solid rocket transport coefficient viscosity coefficient thermal conductivity solid propellant
分类号:
V435
DOI:
10.12115/j.issn.1004-499X(2020)01-008
文献标志码:
A
摘要:
为了解决固体火箭推进剂高温高压燃气输运系数难以实验测量和理论预估的实际问题,考虑燃气中含有H2O、HCl、SO2等强极性组分和H2等轻质组分,通过大量文献实例验证,归纳了适于这些组分及其混合物在高温高压条件下的黏性系数和导热系数计算方法,计算了双基推进剂(DB)、改性双基推进剂(CMDB)和复合推进剂(CP)3种主要固体推进剂燃气在不同温度(1 500~3 800 K)和压强(8~20 MPa)下的黏性系数、导热系数和普朗特数,得到了固体火箭发动机燃气黏性系数和导热系数随温度变化的幂指数函数规律和典型普朗特数取值。所得结果对于促进高温高压气体混合物输运性质的深入研究、火箭发动机燃烧及其内外流动仿真,均具有重要的实际应用意义。该方法没有考虑凝聚相对输运性质的影响。
Abstract:
The transport coefficient of a high-temperature high-pressure combustion gas in solid rocket motor are difficult to be estimated and experimentally verificated. To solve the problem,it was considered that the rocket gas contained strong polar components such as H2O,HCl and SO2,and light components such as H2,and the calculation methods of viscosity coefficient and thermal conductivity of these components and their mixtures under high temperature and high pressure were summarized by a large number of literature examples. The viscosity coefficient,thermal conductivities and Prandtl numbers of three main solid propellant gases of double base propellant(DB),composite modified double base propellant(CMDB)and composite propellant(CP)were calculated at different temperatures(1 500~3 800 K)and pressures(8~20 MPa). The power exponential function law of viscosity coefficient and thermal conductivity changing with temperature and the typical values of Prandtl numbers of solid rocket motor gases were obtained. The obtained result has important practical significance for the in-depth study of promoting the transport properties of high temperature high-pressure gas mixtures,simulation on rocket engine combustion and its internal and external flow. The influence of condensed phase on transport properties is not considered.

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备注/Memo

备注/Memo:
收稿日期:2018-11-27
作者简介:陈军(1969- ),男,副教授,博士,研究方向为新型推进技术。E-mail:cjsky123@njust.edu.cn。
更新日期/Last Update: 2020-03-30