摘要
飞行器红外成像仿真需要不同飞行条件下的温度场分布。本文利用标准(Standard)k-ε模型、剪切应力传输(SST)k-ε模型和Spalart-Allmaras(S-A)模型分别进行数值模拟仿真计算,研究不同飞行速度和飞行高度下的飞行器温度场分布,并对不同模型的结果进行对比分析。首先,利用MultiGen Creator软件对飞行器进行三维建模;其次采用Hypemesh软件和Fluent meshing软件中进行面网格划分和体网格划分,最后采用Fluent 2022R1软件仿真飞行器静态温度场分布,通过改变湍流模型与边界条件设置,对不同飞行速度和不同高度下飞行器温度场进行数值模拟仿真,并与理论结果进行了对比分析。实验结果显示,3种湍流模型均能较好的模拟飞行器蒙皮与尾喷管内壁壁面温度值。飞行器蒙皮温度随着飞行马赫数的增加不断升高;随着飞行高度的升高而不断地降低,与理论结果变化规律一致。在尾喷管内壁面温度仿真中,3种湍流模型仿真的内壁面温度最高相差21 K,相对误差在1.8%左右,在红外仿真中近似忽略不计,故3种湍流模型均适合尾喷管内壁面温度场仿真。在蒙皮温度场仿真中,3种湍流模型仿真计算的蒙皮平均温度值与理论温度值的相对误差均在5%以内,均可满足红外成像仿真的温度差值要求,其中k-ε模型在蒙皮温度场模拟中与理论温度值最为接近,因此k-ε模型精度更高,更适合于飞行器的流场仿真,能更好地仿真出空气动力加热对飞行器温度场的影响。
The infrared imaging simulation of aircraft requires temperature field distribution under different flight conditions.In this study,the Standard k-εModel,SST k-εmodel and S-A model are used to simulate the temperature field of the aircraft respectively,and the simulation accuracy and difference of the temperature field of the three turbulence models at different flight speeds and flight heights are studied.Further comparison with the theoretical values is made to select a suitable simulation model of the temperature field of the aircraft,in order to provide an important reference for the infrared imaging simulation of the aircraft.Firstly,MutiGen Creator software is used to establish the three-dimensional geometric modeling of the aircraft.Secondly,surface mesh and volume mesh are generated in Hypemesh software and fluent mesh software in turn.Finally,Fluent 2022R1 software is used to simulate the static temperature field distribution of the vehicle,and the temperature field of the vehicle is simulated under different flight speeds and different altitudes by changing the turbulence model and the boundary condition settings,and compared with the theoretical results.By changing the turbulence model and boundary condition settings,the temperature field of the aircraft at different flight speeds and different altitudes is simulated numerically and compared with the theoretical results.The experimental results show that the three turbulence models can simulate the temperature of the inner wall of the nozzle and the skin of the aircraft better.The temperature of the skin of the aircraft rises with the increase of the flight Mach number,and decreases with the increase of the flight altitude,which is consistent with the theoretical results.In the tail nozzle inner wall surface temperature simulation,three kinds of turbulence model simulation of the inner wall surface temperature of the highest difference of 21 K,the relative error in 1.8%or so,in the infrared simulation of the approximate negligible,so the three kinds
作者
范福强
邢素霞
张俊举
FAN Fu-qiang;XING Su-xia;ZHANG Jun-ju(Artificial Intelligence Institute,Beijing Technology and Business University,Beijing 100048,China;College of Electronic Engineering and Optoelectronics Technology,Nanjing University of Science and Technology,Nanjing 210094,China)
出处
《激光与红外》
CAS
CSCD
北大核心
2024年第5期766-773,共8页
Laser & Infrared
