摘要
目的 对用于有控火箭飞行方向控制动力的燃气发生器壳体进行非线性瞬态温度场有限元分析； 方法 用有限元法模拟热试验的实际热负荷历程时，考虑燃烧室圆筒段内壁含绝热层和不含绝热层但内壁加厚两种不同试验样机的结构特点，同时考虑结构材料热传导、热容等的温度非线性特点； 结果 给出了燃气发生器燃烧室壳壁的瞬态温度场数值计算结果； 结论 数值计算结果表明两种结构模式都具有足够的热安全性，计算预示的结构特征点温度值与试验所测结果基本相符；
Aim To analyze the transient temperature distribution on the case of a hot gas generator for controllable rockets by nonlinear thermodynamic finite element analysis.Methods Nonlinear thermal characteristics of the structure material and two designed structure models with different heat insulating layers and different thickness of combustion chamber walls were considered during the numerical simulation of the thermal history on test bed. Results Numerical distribution of the transient temperature field on the case of the generator was given. Conclusion Numerical results show that there exists enough thermal safety of the two structure models. The temperature of the characteristic special points predicted by FEA agrees with that measured in test.
出处
《北京理工大学学报》
EI
CAS
CSCD
1999年第S1期120-123,共4页
Transactions of Beijing Institute of Technology
基金
.NULL.
关键词
固体火箭发动机
燃气发生器
有限元分析
热动力分析
结构强度
solid propellant rocket motor
hot gas generator
finite element analysis(FEA)
thermodynamic analysis
structure strength
