Numerical Simulation of Integrated Aeroheating-Structural Heat Transfer Study for Blunt Body

Journal of Propulsion Technology ›› 2019, Vol. 40 ›› Issue (1): 33-43.

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Numerical Simulation of Integrated Aeroheating-Structural Heat Transfer Study for Blunt Body

College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

钝体外形气动加热与结构传热一体化数值模拟

李佳伟,王江峰,杨天鹏,李龙飞,王钰涵

南京航空航天大学航空宇航学院，江苏南京 210016,南京航空航天大学航空宇航学院，江苏南京 210016,南京航空航天大学航空宇航学院，江苏南京 210016,南京航空航天大学航空宇航学院，江苏南京 210016,南京航空航天大学航空宇航学院，江苏南京 210016

作者简介:李佳伟，博士生，研究领域为高超声速力 /热/结构多场耦合。 E-mail: ljwnuaa2010@nuaa.edu.cn 通讯作者:王江峰，博士，教授，研究领域为高超声速力 /热/结构多场耦合。
基金资助:
国家自然科学基金( 90716031)；江苏省研究生科研与实践创新计划项目( KYCX17_0235)。

Abstract

Abstract: In order to improve the efficiency and accuracy in steady numerical simulation of the multi-phys.ical coupling of aerodynamic heating and thermal protection structure heat transfer，an integrated aeroheating-structural thermal numerical method based on finite volume method is applied to the analysis of aerodynamically heated hypersonic blunt body. The uniform governing equations are used in the fluid and structure domains， which are realized by using an up-wind finite volume method，LU-SGS implicit time-stepping scheme and adap.tive unsteady time-step size. This approach does not require extensive post-processing to transfer data，avoiding the computational complexity in the interdisciplinary coupling and interactions. To demonstrate its feasibility and reliability，applications for .uid-thermal-structural analysis of 2D/3D blunt body in steady and unsteady states， are performed and discussed. At 2s，the stagnation temperature of cylinder is about 390.2K. The property distribu.tions of temperature and heat flux are obtained and the time-variant characteristics are analyzed in excellent agreement with the references and experiments. At the same time the steady-state fluid-structural-thermal char.acteristics of 3D blunt body are analyzed，the computed results show that the maximum outer surface temperature of the blunt body structure reaches 535.6K. The numerical simulation results indicate that the integrated approach can offer the potential for signification improvements and efficiency in predicting fluid-structural-thermal prob.lems of long-endurance high speed vehicles，which provide theoretical and technical support for the design of thermal protection structure.

Key words: Aero-heating； Structural heat transfer； Integrated method； Long-endurance； Numerical simulation

摘要： 为了提高气动加热与热防护结构传热多物理场数值模拟的稳态计算效率与计算精度，发展了一种基于有限体积法的气动加热与结构传热一体化数值计算方法。该方法将高速流场与结构温度场统一到同一物理场，基于统一的控制方程组，采用基于 LU-SGS隐式时间迭代和自适应时间步长的有限体积方法进行求解，避开了传统气动加热与结构传热耦合求解方法在时间域内的所需繁琐数据交替迭代策略。对二维 /三维钝体进行一体化数值计算分析，计算结果表明:二维钝体非稳态下，得到 2s时圆管驻点温度最高达到 390.2K，驻点热流密度和结构温度与参考文献和实验值吻合较好，证明了方法的可靠性和可行性。同时分析了三维钝体应用算例的流 -固-热稳态计算特征，计算得到稳态时钝头体结构外壁表面最高温度达到 535.6K，表明一体化计算方法可用于长航时飞行条件下的气动加热 -结构传热多物理场耦合计算分析，为高速飞行器热防护结构设计与选材提供一定的理论与技术支持。

关键词: 气动加热；结构传热；一体化方法；长航时；数值模拟

LI Jia-wei,WANG Jiang-feng,YANG Tian-peng,LI Long-fei,WANG Yu-han. Numerical Simulation of Integrated Aeroheating-Structural Heat Transfer Study for Blunt Body[J]. Journal of Propulsion Technology, 2019, 40(1): 33-43.

李佳伟,王江峰,杨天鹏,李龙飞,王钰涵. 钝体外形气动加热与结构传热一体化数值模拟[J]. 推进技术, 2019, 40(1): 33-43.

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Numerical Simulation of Integrated Aeroheating-Structural Heat Transfer Study for Blunt Body

钝体外形气动加热与结构传热一体化数值模拟

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