Thermal protection performances of metallic honeycomb panel structure at transient thermal shock environment

WU Da-fang; ZHOU An-feng; ZHENG Li-ming; PAN Bing; WANG Yue-wu

doi:10.13224/j.cnki.jasp.2014.06.002

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Thermal protection performances of metallic honeycomb panel structure at transient thermal shock environment

更新时间：2026-07-07

- Thermal protection performances of metallic honeycomb panel structure at transient thermal shock environment
- Issue 6, (2014)
- 作者机构：
  
  1. 北京航空航天大学航空科学与工程学院,北京,100191
  2. 北京航空航天大学宇航学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.06.002
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
吴大方, 周岸峰, 郑力铭, 潘兵, 王岳武. 瞬态热冲击环境下金属蜂窝板结构的热防护特性[J]. 航空动力学报, 2014, (6): 1261-1271. doi: 10.13224/j.cnki.jasp.2014.06.002

WU Da-fang, ZHOU An-feng, ZHENG Li-ming, et al. Thermal protection performances of metallic honeycomb panel structure at transient thermal shock environment[J]. 2014, (6).
吴大方, 周岸峰, 郑力铭, 潘兵, 王岳武. 瞬态热冲击环境下金属蜂窝板结构的热防护特性[J]. 航空动力学报, 2014, (6): 1261-1271. doi: 10.13224/j.cnki.jasp.2014.06.002 DOI：

WU Da-fang, ZHOU An-feng, ZHENG Li-ming, et al. Thermal protection performances of metallic honeycomb panel structure at transient thermal shock environment[J]. 2014, (6). DOI： 10.13224/j.cnki.jasp.2014.06.002.

摘要

使用自行研制的高速飞行器瞬态气动热试验模拟系统，对金属蜂窝板结构在多种瞬态热冲击速率下（5℃/s至30℃/s）的隔热特性进行了试验研究，其中最高瞬时温度达到950℃.并采用三维有限元方法对金属蜂窝板结构在高速热冲击环境下的隔热特性进行了数值计算，其计算结果与试验结果吻合性良好，验证了试验方法以及数值模拟方法的可信性和有效性.由试验知金属蜂窝板结构经过950℃热冲击后的翘曲和扭曲变形均很小，特别适合用于制作在高温环境下，要求变形小、质量少的高速飞行器结构部件.

Abstract

By using a self-developed transient aerodynamic thermal simulation system of high-speed aircraft

the heat-shielding performance of metallic honeycomb panel structure was tested at different transient thermal shock rates ranging from 5℃/s to 30℃/s

with the maximum instantaneous temperature reaching 950℃. Furthermore

a three-dimensional finite element method was established to determine the heat-shielding performance of the metallic honeycomb panel structure at different simulation environments with high thermal shock rates. The numerical calculation results coincide with the corresponding experimental results

verifying the credibility and effectiveness of the experimental methods and the numerical calculation approach. The tested metallic honeycomb panel structure exhibited slight planar flexure and deformation after the experiment in the high-temperature (950℃) environment; thus

in the context of high-speed flight vehicles

this structure is particularly suitable for structural components that must be made of lightweight materials with slight deformation in a high-temperature environment.

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