高超声速飞行器碳基结构高温应变测量

doi:10.7527/S1000-6893.2022.27733

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高超声速飞行器碳基结构高温应变测量

吴东, 杨鸿(), 赵文峰, 罗跃

中国空气动力研究与发展中心超高速空气动力研究所，绵阳 621000

收稿日期:2022-06-30 修回日期:2022-07-27 接受日期:2022-08-27 出版日期:2022-12-25 发布日期:2022-09-13
通讯作者: 杨鸿 E-mail:yanghong@cardc.cn
基金资助:
国家级项目

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

Dong WU, Hong YANG(), Wenfeng ZHAO, Yue LUO

Hypervelocity Aerodynamics Institute，China Aerodynamics Research and Development Center，Mianyang 　621000，China

Received:2022-06-30 Revised:2022-07-27 Accepted:2022-08-27 Online:2022-12-25 Published:2022-09-13
Contact: Hong YANG E-mail:yanghong@cardc.cn
Supported by:
National Level Project

摘要/Abstract

摘要：

高超声速飞行器结构热应力影响巨大，同时高超声速飞行器高温结构使用碳基材料较多，在碳基材料结构上开展高温应变测量分析就变得非常重要。针对碳基材料上应变计的可靠安装和应变计的热特性差异，开展了碳基材料上高温应变测量研究和碳基端头模型高温应变测量应用试验。碳基材料上高温应变测量研究针对粘贴和喷涂等4种不同安装工艺开展了研究，并针对高温流场环境开展了碳基平板高温应变测量验证试验，应变测量最高温度达900 ℃。应用试验在电弧风洞模拟的高温流场中对碳基端头模型进行了高温应变测量，应变测量温度最高为850 ℃，并开展了有限元计算结果对比，验证了高温应变测量结果。碳基端头模型内腔最大压应力值为220 MPa，应变测量结果显示端头模型的应力状态正常。

关键词: 高超声速, 热应力, 碳基材料, 风洞, 喷流

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

中图分类号:

V411.4

吴东, 杨鸿, 赵文峰, 罗跃. 高超声速飞行器碳基结构高温应变测量[J]. 航空学报, 2022, 43(S2): 160-169.

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): 160-169.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

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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高超声速飞行器碳基结构高温应变测量

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

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