Uncertain structural analysis of solid propellant grain and comparison of the methods

LIU Dong-qing; SUN Bing; ZHANG Jian-wei

Chinese

您当前的位置：

首页 >

文章列表页 >

Uncertain structural analysis of solid propellant grain and comparison of the methods

更新时间：2026-07-07

- Uncertain structural analysis of solid propellant grain and comparison of the methods
- Vol. 28, Issue 2, (2013)
- 作者机构：
  
  北京航空航天大学宇航学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2013
- 稿件说明：
移动端阅览
LIU Dong-qing, SUN Bing, ZHANG Jian-wei. Uncertain structural analysis of solid propellant grain and comparison of the methods[J]. 2013, 28(2).
DOI：

LIU Dong-qing, SUN Bing, ZHANG Jian-wei. Uncertain structural analysis of solid propellant grain and comparison of the methods[J]. 2013, 28(2). DOI：

摘要

针对复合固体推进剂力学性能参数的不确定性对固体火箭发动机药柱结构分析的影响

使用软件ANSYS parametric design language(APDL)建立了受固化降温载荷和压力载荷联合作用下药柱结构的参数化有限元模型.在此基础上

分别应用蒙特卡洛法和响应面法

研究了复合固体推进剂热膨胀系数与初始泊松比的随机分布对药柱结构有限元分析的影响

并对两种方法得到的概率分析结果进行了对比.结果表明:复合推进剂热膨胀系数和初始泊松比微小的变化会对结构分析结果产生较大的影响;药柱结构响应对初始泊松比更为敏感.在药柱结构有限元分析时考虑推进剂力学性能参数的不确定性十分必要.通过对两种不确定结构分析方法的比较发现

响应面法得到的分析结果与蒙特卡洛法得到的分析结果十分接近

且分析效率远高于蒙特卡洛法.

Abstract

Concerning the influence of uncertainty in composite solid propellant's mechanical properties on structural analysis of solid rocket motor(SRM) grain

the parameterized finite element model of SRM grain under temperature and pressure loading is constructed through ANSYS parametric design language (APDL).On that basis

the influence of random distribution of composite solid propellant's thermal expansion coefficient and initial Poisson's ratio on finite element structural analysis of SRM grain is studied with Monte-Carlo method and response surface method.Results of the two different methods are compared.The results show that small changes in composite solid propellant's thermal expansion coefficient and initial Poisson's ratio cause relatively great influence on the results of structural analysis and the structural responses of the propellant grain are more sensitive to initial Poisson's ratio.So

uncertainty in composite solid propellant's mechanical properties should be considered during finite element structural analysis of SRM grain.It is indicated by the comparison of this two kinds of methods that response surface method can give approximately the same results as those from Monte-Carlo method and is greatly more efficient than Monte-Carlo method.

关键词

Keywords

references

Views

1095

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Optimization design for nozzle contour of rocket engine based on response surface method

Integrated aerodynamic optimization design of convergent-divergent nozzle and vehicle afterbody

Computational method of ball bearing’s service-reliability ratio based on LS-DYNA

Estimation of relaxation modulus of composite solid propellant based on particle packing model

与发动机匹配的旁路式双喉道气动矢量喷管数值模拟研究

Related Author

Yihua XU

Haijun SUN

Xiping FENG

Yingpeng WANG

康娜

韩龙

许进升

郑健

Related Institution

Jiangxi Key Laboratory of Micro Aeroengine，School of Aircraft Engineering， Nanchang Hangkong University

Science and Technology on Combustion，Internal Flow and Thermo⁃Structure Laboratory，Northwestern Polytechnical University

南京理工大学机械工程学院

中国兵器工业集团北方华安工业集团有限公司

School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰