固体火箭发动机喷管热结构一体化计算

郑晓亚; 王卫祥; 蔡飞超; 陈凤明

固体火箭发动机喷管热结构一体化计算

1.
西北工业大学航天学院, 西安 71007
2.
中国航天科工集团第九总体设计部, 武汉 430040

基金项目: 装备预研基金项目(9140A28010112HK03320); 2009年航天支撑技术基金

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出版历程
- 收稿日期: 2011-09-26
- 刊出日期: 2012-09-28

Thermo-structure integrative computation for nozzle in SRM

1.
School of Astronautics, Northwestern Polytechnical University, Xi'an 71007
2.
The 9th Designing of China Aerospace Science Industry, Wuhan 430040, China

摘要

摘要: 基于user-defined function(UDF)技术将固体火箭发动机喷管热结构计算程序嵌入到FLUENT软件中,通过UDF宏命令实现FLUENT耦合传热结果数据的提取,编写了接触边界的自动识别程序,采用直接约束法模拟喷管界面间的接触非线性问题,实现了固体火箭发动机喷管热结构的一体化计算.
- 航空航天推进系统 /
- 固体火箭发动机喷管 /
- 热结构 /
- 耦合传热 /
- 接触非线性
Abstract: The thermo-structure computation procedure of nozzle in SRM(solid rocket motor) was embedded in software FLUENT based on user-defined function (UDF). It realized coupled heat transfer data picked using UDF macro commands.Contact boundary identify procedure was complied and direct constraint method was applied to solve boundary nonlinear problem.Then it achieved thermo-structure integrative computation for nozzle in SRM.
- aerospace propulsion system /
- solid rocket motor nozzle /
- thermo-structure /
- coupled heat transfer /
- contact nonlinearity

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参考文献(12)

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