固体火箭发动机尾喷管复合堵盖数值模拟研究

Numerical simulation study about nozzle composite closure of solid rocket engine

基于一种固体火箭发动机耐高温尾喷管复合堵盖设计,利用Abaqus有限元软件对该复合堵盖在相同外界条件、不同防热结构下的力学特性以及传热效应进行三维数值模拟研究。结果表明:对于未采用WL-640绝热材料包覆的铝堵盖在0.2 MPa正向压强作用下其根部最大应力值为45.2 MPa,沿厚度方向最大位移量为10.66 mm;对于采用绝热材料包覆的铝堵盖,其最大应力值、表面温度以及沿厚度方向的位移量随绝热材料厚度的增加而减小。根据计算结果,在需充分考虑材料性能及使用工况的前提下,采用文中所述的一种复合堵盖设计,能够提高导弹在特定飞行工况下固体火箭发动机尾喷管堵盖的耐热性以及其工作可靠性。

Based on a high temperature-resistance nozzle composite closuredesign of Solid Rocket Engine,Abaqus finite element software was used to study its structural characteristics and heat transfer effect of under same external conditions and different thermal structure design by three-dimensional numerical simulation.The result shows that the aluminum closure maximum stress is 45.2 MPa,the displacement along the thickness direction of the aluminum closure without WL-640 insulation material is 10.66 mm.The maximum stress,temperature and displacement along the thickness direction of the aluminum closure covered by WL-640 insulation material will decrease with the increase of insulation material.According to the calculation conditions described in this paper,on the premise of fully considering the material properties and working conditions,the nozzle composite closure described in this paper can improve the heat resistance and work reliability of the solid rocket engine nozzle closure under certain flight conditions of missile.