摘要
以某超声速飞行器头部壳体为研究对象,采用气动加热工程算法求解飞行器头部壳体表面热流分布情况,利用有限元分析软件,在考虑飞行器头部壳体材料热物性参数的情况下,模拟出气动加热的热量由飞行器头部壳体结构壁面向内导热不同时刻在飞行器头部壳体的温度场分布。采用工程计算和模拟仿真相结合的技术进行高速飞行器气动加热计算,融合两种方法优点,克服彼此局限性,最终得到不同飞行时刻飞行器头部的温度场分布,为飞行器的结构设计、热防护设计、材料选择以及飞行安全性评估提供参考依据。
Taking a supersonic aircraft head shell for the study,aerodynamic heating engineering algorithm is used to solve the heat flux distribution on the surface of the aircraft head. The finite element analysis software is used considering the aircraft head shell material thermal physical parameters. The temperature field distribution of aircraft head shell at different times is simulated when the heat of the aerodynamic heating up conduct inward from the aircraft head shell wall structure. With the combination of engineering calculation and simulation,the calculation of aerodynamic heating of high speed aircraft is carried out,and the advantages of the two methods are combined to overcome the limitation of each other,the temperature field distribution of the aircraft head at different flight time was obtained finally,which can provide reference for aircraft structure design,thermal design,material selection and flight safety assessment.
作者
焦新泉
李照华
贾兴中
Jiao Xinquan;Li Zhaohua;Jia Xingzhong(National Key Laboratory for Electronic Measurement Technology, North University of China, Taiyuan 030051, China)
出处
《战术导弹技术》
北大核心
2017年第5期36-40,共5页
Tactical Missile Technology
关键词
气动加热
工程算法
有限元分析
aerodynamic heating
engineering algorithm
finite element analysis
