摘要
本文依据柔性配方的环氧树脂基(改性环氧树脂)碳纤维复合材料的实验数据,对固体火箭发动机壳体进行有限元分析。首先根据网格理论推导出螺旋向纤维在筒身段缠绕角及缠绕层数的表达式。然后根据推导出的公式计算出相应的参数,并依据计算所得结果设置合理的铺层方案。最后利用ANSYS软件进行建模,并对模型进行有限元分析,从而得到复合材料压力容器随内压的增加,内衬层以及纤维缠绕层应力的变化趋势,并最终得到模型的爆破极限,进而证明了ANSYS软件在复合材料压力容器模拟方面具有实用性与可靠性。
The article according to a flexible formula of epoxy resin-based(modified epoxy)carbon fiber composite materials experimental data to analyze the finite element of a solid rocket motor housing.Firstly,according to the grid theory,to derivate the expression of the thickness of the spiral fillet and the spiral wound in the head section of the winding angle.Then,according to the formula to calculate the corresponding to the parameters,and according to the calculation results set reasonable layer solution.Finally,using ANSYS software to model,and doing the finite element analysis for the model.It is show that the stress of the composite pressure vessel increases with the increase of the internal pressure,the lining layer and the stress of the fiber wound layer,and finally got the blasting limit of the composite pressure vessel,and it proves that ANSYS software has practicality and reliability in the simulation of composite pressure vessel.
出处
《内蒙古工业大学学报（自然科学版）》
2017年第4期255-260,共6页
Journal of Inner Mongolia University of Technology：Natural Science Edition
