力热联合载荷下炭纤维缠绕壳体轴压稳定性分析

Analysis of axial compression stability of carbon fiber composite shell at heat combined loading conditions

为了研究炭纤维缠绕壳体在力热联合载荷下的轴压稳定性,通过试验测试了炭纤维复合材料单层板在不同温度下的弹性常数,计算出炭纤维复合材料壳体在不同温度下的等效弹性常数。基于层合板理论计算了炭纤维复合材料壳体的临界轴压,设计了力热联合载荷下炭纤维缠绕壳体试验方案,测试了壳体在不同温度下的轴压破坏载荷。结果表明,炭纤维复合材料壳体的临界轴压随温度升高逐渐降低;当使用温度超过树脂玻璃化温度后,壳体轴压破坏载荷呈指数级下降;在临界轴压理论计算公式的基础上取修正系数为0.04,可准确预示炭纤维复合材料壳体的轴压破坏载荷。相关结论和方法可为固体发动机复合材料壳体和外防热结构设计提供依据。

In order to study the axial compression stability of the carbon fiber wound shell under the combined stimulus of heat and heat,the elastic constant of the carbon fiber composite single-layer board at different temperatures has been measured by the tensile test,and the parameters for carbon fiber composite shell was calculated at different temperatures.Based on the theory of laminated plates,the critical axial pressure of carbon fiber composite shell was calculated.The test plan of carbon fiber wound shell under combined force and heat loading was designed.The axial compressive failure load of the shell at different temperatures was finally tested.The results show that the critical axial pressure of carbon fiber composite shell decreases with the increase of temperature.If the service temperature exceeds the glass transition temperature of the resin,the axial compressive load of the shell decreases exponentially.Based on the theoretical calculation formula of critical axial pressure,the correction coefficient is 0.04,which can accurately predict the axial compression failure load of the carbon fiber composite shell.Relevant conclusions and methods can provide a basis for the design of solid engine composite shell and external heat shield structure.