高热环境下前缘结构高温应变测量  

High temperature strain measurement of the front edge structure in high thermal environment

作　　者：吴东[1] 陈德江[1] 周玮[1] 杜百合[1] 

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,四川绵阳621000

出　　处：《实验流体力学》2016年第3期92-97,共6页Journal of Experiments in Fluid Mechanics

基　　金：热结构热匹配试验技术研究(36092020302)

摘　　要：高超声速飞行器前缘在大气层中长时间飞行时受热严酷,热应力影响大,分析前缘结构热应力十分必要。在电弧风洞模拟的高热环境下采用高温应变计对高超声速飞行器前缘结构进行了高温应变测量,介绍了试验设备、试验条件、试验模型和热输出标定等,并介绍分析了碳基复合材料和某耐热合金2种材料前缘模型试验结果,同时对比了有限元计算结果,表明测量结果真实。试验应变测量最高温度600℃,试验结果表明,前缘模型侧面平板的应力状态处于合理水平。应力应变数据对于结构优化设计起到了重要作用。During the long time flight in the aerosphere,the hypersonic vehicles＇ front edge structures are heated badly and affected greatly by thermal stress.Therefore it is necessary to analyze the stress field of the front edge structure.The hot structure experiment of hypersonic vehicles＇ front edge was done in the arc heated wind-tunnel.During the experiment high temperature strain was measured using the high temperature strain gages.In this paper,the experimental equipment,the experimental condition,the experimental model and calibration of thermal output are introduced.The experimental data of two kinds of model materials including carbon composite and heat-resistant alloy are analyzed.The computational results verifies the experimental data.The temperature of the experimental strain measurement was 600℃.The experimental results show that the front edge model＇s side flat is in a normal stress state.The results shall be an important reference for structure optimization design.

关 键 词：高超声速 应力 应变 风洞 高温 测量 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]