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分别开展缝合气凝胶夹芯复合材料在不同温度下的面内压缩试验,研究材料在室温、300℃、600℃和800℃下的面内压缩力学性能,并采用微焦点工业CT扫描的方法对试样内部结构进行分析,结合有限元分析方法,探究其结构破坏机制。结果表明:在面内压缩载荷作用下,材料存在极限载荷,面板的局部屈曲、芯层的剪切破坏以及缝线柱的断裂是材料破坏的主要方式。随着温度的升高,材料的面内压缩模量和极限载荷也逐渐升高,面板破坏处的断口逐渐呈现出类似脆性的断裂。300℃、600℃和800℃下材料的面内压缩模量分别为室温的1.05倍、1.57倍和1.65倍;极限载荷分别为室温的1.14倍、1.46倍和1.67倍。室温下有限元分析结果和试验结果的对比,验证了缝合气凝胶夹芯复合材料面内压缩破坏模式的合理性。
The in-plane compressive tests of suture airgel sandwich composites at different temperatures were carried out respectively. The in-plane compressive mechanical properties of the composites at room temperature, 300 ℃, 600 ℃ and 800 ℃ were studied. The micro-focus industrial CT scanning method Analysis of the internal structure of the sample, combined with the finite element analysis to explore the mechanism of structural damage. The results show that under the action of in-plane compressive load, the material has ultimate load. The local buckling of the panel, the shear failure of the core layer and the fracture of the suture thread are the main ways of material failure. With the increase of temperature, the in-plane compressive modulus and ultimate load of the material also gradually increase, and the fractures at the panel failure gradually show brittle fracture. The in-plane compressive modulus at 300 ℃, 600 ℃ and 800 ℃ are 1.05 times, 1.57 times and 1.65 times respectively, and the ultimate loads are 1.14 times, 1.46 times and 1.67 times respectively at room temperature. The comparison of finite element analysis results and experimental results at room temperature verifies the rationality of the in-plane compression failure modes of stitched airgel sandwich composites.