摘要
固化降温过程是固体火箭发动机装药制造过程中的一个重要环节,固化降温过程中各界面热应力的产生将直接影响装药性能,为此建立了装药数学模型和物理模型。基于粘弹性积分型本构关系,应用有限元分析软件,数值模拟固体火箭发动机装药的固化降温过程,得到固体推进剂在固化降温过程中应力、应变的变化规律。仿真结果对分析装药固化降温过程中的结构完整性有很好的参考价值。
Cooling process after curing is a very pivotal step during manufacturing the SRM＇s grain, and the thermal stress of different interface can affect directly the mechanical capability of the solid rocket motor＇s grain. Mathematics and physical models of the grain were built up. Based on the viscoelastic integral constitutive relation, the cooling process after curing of the SRM＇s grain was simulated by using the finite element software. The variation regulation of the equivalent stress and strain was obtained. The result has a good reference value in analyzing the construction of the SRM＇s grain during cooling process after curing.
出处
《导弹与航天运载技术》
北大核心
2015年第1期104-106,共3页
Missiles and Space Vehicles
基金
学院科研发展基金项目资助(43454171)
关键词
固体火箭发动机
温度场
固化降温
应力场
Solid rocket motor
Temperature field
After-cure cooling
Stress field
