Simulation and design of thermal protection of rocket motor in certain detector

ZHANG Tao; SUN Bing

Chinese

您当前的位置：

首页 >

文章列表页 >

Simulation and design of thermal protection of rocket motor in certain detector

更新时间：2026-07-07

- Simulation and design of thermal protection of rocket motor in certain detector
- Vol. 25, Issue 6, (2010)
- 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：2010
- 稿件说明：
移动端阅览
ZHANG Tao, SUN Bing. Simulation and design of thermal protection of rocket motor in certain detector[J]. 2010, 25(6).
DOI：

ZHANG Tao, SUN Bing. Simulation and design of thermal protection of rocket motor in certain detector[J]. 2010, 25(6). DOI：

摘要

根据某探测器的具体结构及工作条件

分析和计算探测器上火箭发动机的热环境参数.利用有限元法计算火箭发动机固壁辐射热流密度

依据热流边界条件设计热防护方案;利用有效发射率表征多层隔热材料隔热性能并进行温度场数值仿真.由于多层隔热材料性能参数的不易确定性

计算了参数在较大范围内的热防护效果.通过仿真计算验证热防护方案的有效性和可靠性

并分析影响热防护效果的主要因素;计算结果表明多层隔热材料的有效发射率是影响隔热性能最重要的因素

比热容、表面发射率、密度对热防护性能影响很小.

Abstract

Heat environment parameters of rocket motor were analyzed and computed based on structure and work condition of certain detector.Solid radiation heat flux of rocket motor was computed by finite element method

and thermal protection scheme was designed according to heat flux boundary condition.Multilayer insulation material performance was expressed by equivalent emissivity and temperature field was simulated.As the performance parameters are difficult to determine

the temperature field was computed in wide parameter range.Efficiency and reliability of thermal protection scheme were validated and primary influential factors to thermal protection performance were analyzed

providing a theoretical basis for design and selection of thermal protection scheme.

关键词

Keywords

references

Views

495

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Investigation on thermal environment for deep-space-exploration liquid rocket engine

Cooling performance of hydrogen for transpiration cooling structure made by different materials

Experiment and simulation on aircraft thermal protection and utilization integrated system

Simulation study on combustion flow in low⁃pressure condition of hydrogen⁃oxygen torch ignitor

Influence of different geometric structures on thermal protection characteristics of fuel nozzle

Related Author

WEI Chao

ZHANG Zhong-li

Jiguo SUN

Guobiao CAI

Wei XU

Junwei ZHAO

Benli YUAN

Rui LONG

Related Institution

School of Astronautics, Northwestern Polytechnical University

Xi'an Aerospace Propulsion Institute, Academy of Aerspace Propulsion Technology

School of Astronautics，Beihang University

School of Energy and Power Engineering，Huazhong University of Science and Technology

Department of Aerospace Business，China Academy of Launch Vehicle Technology， China Aerospace Science and Technology Corporation

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