Full Text:   <3071>

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CLC number: V21

On-line Access: 2014-03-04

Received: 2013-10-17

Revision Accepted: 2014-01-17

Crosschecked: 2014-02-20

Cited: 5

Clicked: 6385

Citations:  Bibtex RefMan EndNote GB/T7714

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Journal of Zhejiang University SCIENCE A 2014 Vol.15 No.3 P.185-196


Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles*

Author(s):  Yuan-chun Liu1, Yu-rong He1, Jia-qi Zhu2, Jie-cai Han2, Dong-liang Quan3

Affiliation(s):  1. School of Energy Science & Engineering, Harbin Institute of Technology, Harbin 150001, China; more

Corresponding email(s):   rong@hit.edu.cn

Key Words:  Chemical vapor deposition (CVD) ZnS, Infrared window material, Thermal and stress responses, Hypersonic vehicles

Yuan-chun Liu, Yu-rong He, Jia-qi Zhu, Jie-cai Han, Dong-liang Quan. Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles[J]. Journal of Zhejiang University Science A, 2014, 15(3): 185-196.

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author="Yuan-chun Liu, Yu-rong He, Jia-qi Zhu, Jie-cai Han, Dong-liang Quan",
journal="Journal of Zhejiang University Science A",
publisher="Zhejiang University Press & Springer",

%0 Journal Article
%T Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles
%A Yuan-chun Liu
%A Yu-rong He
%A Jia-qi Zhu
%A Jie-cai Han
%A Dong-liang Quan
%J Journal of Zhejiang University SCIENCE A
%V 15
%N 3
%P 185-196
%@ 1673-565X
%D 2014
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A1300341

T1 - Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles
A1 - Yuan-chun Liu
A1 - Yu-rong He
A1 - Jia-qi Zhu
A1 - Jie-cai Han
A1 - Dong-liang Quan
J0 - Journal of Zhejiang University Science A
VL - 15
IS - 3
SP - 185
EP - 196
%@ 1673-565X
Y1 - 2014
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A1300341

hypersonic vehicles subjected to strong aerodynamic forces and serious aerodynamic heating require more stringent design for an infrared window. In this paper, a finite element analysis is used to present the distributions of thermal and stress fields in the infrared window for hypersonic vehicles based on flowfield studies. A theoretical guidance is provided to evaluate the influence of aerodynamic heating and forces on infrared window materials. The aerodynamic heat flux from Mach 3 to Mach 6 flight at an altitude of 15 km in a standard atmosphere is obtained through flowfield analysis. The thermal and stress responses are then investigated under constant heat transfer coefficient boundary conditions for different Mach numbers. The numerical results show that the maximum stress is higher than the material strength at Mach 6, which means a failure of the material may occur. The maximum stress and temperatures are lower than the material strength and melting point under other conditions, so the material is safe.


研究方法:1.计算标准大气情况下,高度为15 km、马赫数分别为3、4、5和6时飞行器的流场;2.根据流场分析得到数据,用有限元法计算红外窗口的热-结构场。


Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article


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