高超声速飞行器碳基结构高温应变测量

doi:10.7527/S1000-6893.2022.27733

Abstract

Abstract:

The hypersonic aircraft structures are affected greatly by thermal stress. The carbon-based composite material is widely used in the high temperature structures of the hypersonic vehicles. Therefore， it is necessary to measure and analyze the high temperature strain field for carbon-based composite material. In view of the reliable installation of strain gage on carbon-based materials and the difference of thermal characteristics of strain gage， high temperature strain measurement research was conducted for carbon-based composite material and end model. The high temperature strain measurement research for carbon-based composite material were conducted considering four kinds of strain gages installation technics including paste and spray. Validation experiments of high temperature strain measurement on carbon-based flat under high temperature flow field were also carried out. The temperature of strain measurement was up to 900 ℃. High temperature strain measurement applicable experiment for carbon-based end model was carried out in the arc heated wind-tunnel up to 850 ℃. The experimental data of carbon-based end model were analyzed and compared by the finite element method， suggesting the reliability of the experimental results. The highest compression stress of carbon-based end model was 220 MPa. The experimental results showed that stress state of carbon end model was normal.

Key words: hypersonic, thermal stress, carbon-based composite material, wind tunnel, spry

CLC Number:

V411.4

Dong WU, Hong YANG, Wenfeng ZHAO, Yue LUO. High temperature strain measurement of hypersonic aircraft carbon-based composite material structures[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 160.

Figures/Tables 16

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References 23

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加载编号	应变计测试数据/με
加载编号	1号	2号	3号	4号
平均值	-463.7	-463.6	467.9	467.1
第1次	-462.6	-462.6	466.5	467.7
第2次	-464.9	-464.5	468.9	467.5
第3次	-463.6	-463.8	468.2	466.1

加载编号	应变计测试数据重复性/%
加载编号	1号	2号	3号	4号
平均值	0.173	0.149	0.195	0.143
第1次	0.237	0.223	0.292	0.128
第2次	0.259	0.187	0.221	0.086
第3次	0.022	0.036	0.071	0.214

校准温度/℃	高温应变计灵敏系数		偏差/%
校准温度/℃	校准值	北科大校准值	偏差/%
室温	2.182	2.20	0.82
200	2.062	2.036	-1.28
400	1.99	1.955	-1.79
600	1.952	1.894	-3.06
800	1.788	1.738	-2.88

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High temperature strain measurement of hypersonic aircraft carbon-based composite material structures

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