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为研究HTPB推进剂在冲击载荷下的能量耗散规律,结合分离式霍普金森压杆(SHPB)搭建了红外测温系统。该系统响应速度快,可同步获取冲击实验中HTPB推进剂表面的温度变化。结果表明,HTPB推进剂受载后表现出粘-超弹特性,并且在高速变形中试件经历了温度的显著升高。在粘-超弹性本构模型的基础上引入温度项,考虑了热软化效应,更加准确地描述了HTPB推进剂在高应变率变形下的热力学响应,可对复合固体推进剂在冲击载荷下的热力耦合分析提供理论支持。
In order to study the energy dissipation of HTPB propellant under impact load, an infrared temperature measurement system was set up based on the split Hopkinson pressure bar (SHPB). The system is fast in response to simultaneous temperature changes on the surface of HTPB propellants during impact experiments. The results show that the HTPB propellant exhibits viscous-super elastic properties when loaded and the specimen undergoes a significant temperature increase during high-speed deformation. Based on the viscous-hyperelastic constitutive model, the temperature term is introduced, the thermosoftening effect is taken into account, and the thermodynamic response of HTPB propellant under high strain rate deformation is more accurately described. The thermodynamic response of the composite solid propellant under impact load Thermodynamic coupling analysis provides theoretical support.