基于SABRE的气动热与瞬态传热耦合分析流程  

Coupled Analysis Process of Aerodynamic Heat and Transient Heat Transfer Based on SABRE

作　　者：郭瑜超[1] 聂小华[1] 许向彦 王立凯[1] GUO Yu-chao;NIE Xiao-hua;XU Xiang-yan;WANG Li-kai(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi'an Shaanxi 710065,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,陕西西安710065

出　　处：《计算机仿真》2025年第3期40-44,共5页Computer Simulation

基　　金：陕西省重点研发计划(2022ZDLGY02-03)。

摘　　要：针对高超声速飞行器翼面结构的气动加热分析问题,研究了翼面前缘驻点区域和翼面一般部位的气动热流密度工程计算方法,并与结构瞬态传热有限元方法结合,设计了气动加热与结构瞬态传热耦合分析策略;研发了典型翼面结构气动热流密度计算模块,并基于自主结构分析软件SABRE的瞬态传热分析流程,构建了气动加热-瞬态热传耦合求解流程;最后,建立某翼面结构的有限元模型进行数值验证,翼面温度场计算结果与相关文献基本一致,说明了分析流程的正确性。Aiming at the aerodynamic heating problem of hypersonic aircraft wing structure,the engineering calculation method of aerodynamic heat flux density in the stagnation point region of the leading edge of the wing and the general part of the wing surface was studied,and the coupling analysis strategy of aerodynamic heating and structural transient heat transfer was designed by combining the finite element analysis method of structural transient heat transfer.The aerodynamic heat flux calculation module of a typical wing structure was developed,and the aerodynamic heating-transient heat transfer coupling solution process was constructed based on the transient heat transfer analysis process of the autonomous structural analysis software SABRE.Finally,the finite element model of a certain wing structure was established for numerical verification.The calculated results of the wing temperature field are basically consistent with the relevant documents,indicating the correctness of the analysis process.

关 键 词：高超声速飞行器 气动加热 工程算法 瞬态传热 耦合分析 

分 类 号：V414.7[航空宇航科学与技术—航空宇航推进理论与工程]