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2222材料工程  2022, Vol. 50 Issue (7): 119-127    DOI: 10.11868/j.issn.1001-4381.2021.000379
  研究论文 本期目录 | 过刊浏览 | 高级检索 |
莫来石纤维增强SiO2气凝胶复合材料压缩回弹性能实验与建模研究
吕双祺1, 黄佳2, 孙燕涛3, 付尧明1, 杨晓光4, 石多奇4,*()
1 中国民用航空飞行学院 航空工程学院, 四川 广汉 618307
2 中南大学 航空航天学院, 长沙 410083
3 北京航空工程技术研究中心, 北京 100076
4 北京航空航天大学 能源与动力工程学院, 北京 102206
Experimental and modeling investigation on compression springback property of mullite fiber reinforced silica aerogel composites
Shuangqi LYU1, Jia HUANG2, Yantao SUN3, Yaoming FU1, Xiaoguang YANG4, Duoqi SHI4,*()
1 Aviation Engineering College, Civil Aviation Flight University of China, Guanghan 618307, Sichuan, China
2 School of Aeronautics and Astronautics, Central South University, Changsha 410083, China
3 Beijing Aeronautical Engineering Technical Research Center, Beijing 100076, China
4 School of Energy and Power Engineering, Beihang University, Beijing 102206, China
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摘要 

对莫来石纤维增强SiO2气凝胶复合材料开展面外方向单轴压缩实验,研究不同极限应变、热暴露温度对压缩回弹行为与变形恢复能力的影响,基于微观结构形貌变化阐释内在机制,对加载和卸载阶段的变形行为建立唯像力学模型。结果表明:莫来石纤维增强SiO2气凝胶复合材料的压缩回弹行为呈现非线性特征,极限应变越大,变形恢复能力越差;高温热暴露预处理会对压缩回弹性能产生影响,热暴露温度越高,变形恢复能力越差,基体颗粒-团簇结构的聚集、大尺寸孔洞的形成和塌陷是主要原因;所建立的唯像力学模型可以用来描述材料在压缩加载-卸载时的应力-应变曲线,拟合结果与实验数据吻合较好。

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吕双祺
黄佳
孙燕涛
付尧明
杨晓光
石多奇
关键词 气凝胶复合材料热防护系统压缩回弹高温力学模型    
Abstract

Uniaxial compression tests were carried out on mullite fiber reinforced silica aerogel composites in the out-of-plane direction. Influences of different ultimate strains and thermal exposure temperatures on the compression springback behavior and deformation recovery capability were investigated. Internal mechanisms based on the microstructure morphology changes were explained. Phenomenological mechanical models were established respectively for the deformation behavior in the loading and unloading stages. The results show that the compression springback behavior of mullite fiber reinforced silica aerogel composites exhibits nonlinear characteristics. The greater the ultimate strain, the worse the deformation recovery capability. High temperature thermal exposure pre-treatment has an effect on the compression springback property, the higher the thermal exposure temperature, the worse the deformation recovery capability. The aggregation of matrix particle-cluster structure and the formation and collapse of the large size holes are main causes. The phenomenological mechanical model can be used to describe the stress-strain curve of the composites during loading and unloading. The fitting results are in good agreement with the experimental data.

Key wordsaerogel composite    thermal protection system    compression springback    high temperature    mechanical model
收稿日期: 2021-04-22      出版日期: 2022-07-18
中图分类号:  TB332  
基金资助:国家自然科学基金(51772009);中国民用航空飞行学院科研基金(J2021-042)
通讯作者: 石多奇     E-mail: shdq@buaa.edu.cn
作者简介: 石多奇(1975—), 男, 教授, 博士生导师, 博士, 研究方向为高温合金和复合材料本构理论、高温结构强度, 联系地址: 北京市昌平区沙河高教园南三街9号国实F座北京航空航天大学能源与动力工程学院(102206), E-mail: shdq@buaa.edu.cn
引用本文:   
吕双祺, 黄佳, 孙燕涛, 付尧明, 杨晓光, 石多奇. 莫来石纤维增强SiO2气凝胶复合材料压缩回弹性能实验与建模研究[J]. 材料工程, 2022, 50(7): 119-127.
Shuangqi LYU, Jia HUANG, Yantao SUN, Yaoming FU, Xiaoguang YANG, Duoqi SHI. Experimental and modeling investigation on compression springback property of mullite fiber reinforced silica aerogel composites. Journal of Materials Engineering, 2022, 50(7): 119-127.
链接本文:  
http://jme.biam.ac.cn/CN/10.11868/j.issn.1001-4381.2021.000379      或      http://jme.biam.ac.cn/CN/Y2022/V50/I7/119
Fig.1  增强纤维在气凝胶基体中面内方向上的随机分布特征
Fig.2  莫来石纤维增强SiO2气凝胶复合材料的显微结构
(a)面内方向上的莫来石纤维和气凝胶基体;(b)SiO2气凝胶基体中的颗粒-团簇结构
Fig.3  莫来石纤维增强SiO2气凝胶复合材料面外压缩试样示意图
Fig.4  纤维增强气凝胶复合材料典型面外压缩应力-应变曲线
Fig.5  莫来石纤维增强SiO2气凝胶复合材料面外压缩应力-应变曲线
Fig.6  莫来石纤维增强SiO2气凝胶复合材料受压后的显微结构(30%应变)
Fig.7  不同极限应变下莫来石纤维增强SiO2气凝胶复合材料的变形恢复能力
Fig.8  不同温度热暴露后莫来石纤维增强SiO2气凝胶复合材料的面外压缩应力-应变曲线
Fig.9  不同温度热暴露后莫来石纤维增强SiO2气凝胶复合材料的变形恢复能力
Fig.10  高温热暴露对显微结构的影响
(a)颗粒和团簇的聚集;(b)基体和纤维之间的粘连
Loading stage Unloading stage
α β γ δ k1 k2 m1 m2
0.9128 1.3399 0.02304 -2.0386 11.1536 0.4982 10.9037 -0.5761
Table 1  加载-卸载阶段模型的材料常数值(室温)
Fig.11  不同极限应变下压缩回弹行为模拟与实验数据对比
(a)30%应变;(b)20%应变;(c)10%应变;(d)5%应变
Temperature/℃ Loading stage Unloading stage
α β γ δ k1 k2 m1 m2
300 1.1986 1.0279 0.0001 -5.7244 4.2407 1.6342 -8.3620 2.9117
600 1.1003 1.3658 0.000005 -8.2758 5.2105 1.840 -56.0690 12.9229
900 0.9817 1.2120 0.1370 0 7.5898 2.3637 -102.2332 23.7712
Table 2  加载-卸载阶段模型的材料常数值(高温)
Fig.12  不同温度热暴露后压缩回弹行为模拟与实验数据对比
(a)300 ℃;(b)600 ℃;(c)900 ℃
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