高超声速助推滑翔飞行器气动热环境仿真分析  

Simulation and analysis of thermal environment calculation for hypersonic boost glide vehicle

作　　者：孟竹喧 胡凡[1] 彭科[1] 张为华 

机构地区：[1]国防科技大学航天科学与工程学院,长沙410073

出　　处：《固体火箭技术》2016年第2期295-300,共6页Journal of Solid Rocket Technology

摘　　要：以高超声速助推滑翔飞行器为对象,研究了基于边界层外缘参数无粘数值解的气动热环境仿真分析问题。建立了高超声速飞行器壁面气动热环境计算模型,对比分析了钝双锥模型壁面气动热环境。结果表明,0°攻角状态下,该文方法与工程方法计算得到迎风面母线热流密度与实验结果相比最大差值分别为1.16%和5.53%;10°攻角状态下最大差值分别为17.3%和53.7%,证明该文气动热计算方法明显优于工程计算方法。对比分析了高超声速助推滑翔飞行器气动热纯数值仿真结果与该文方法的计算结果,热流密度曲线变化趋势一致,且该文方法计算效率明显优于数值方法;并沿弹道进行了气动热仿真分析,为防热结构设计与分析提供了重要依据。In this paper, based on the inviscid outer edge boundary layer parameters, the thermal simulation and analysis of the hypersonic boost glide vehicle was studied. The thermal environment near the wall boundary of hypersonic vehicles was built, and the aerodynamic thermal of blunt double-cone model was calculated and compared. Results show that at the 0° angle of attack, the heat flux along the upwind generatrix calculated by the method proposed in this paper and the engineering method, compared with the test result, have differences of 1.16% and 5.53% respectively, while at the 10°are 17.3% and 53.7% respectively, which proved that the method in this paper has a better accuracy than the engineering method. Results of the calculation by this method and the numerical method were also compared, which coincided well of the tendency in heat flux, in addition, the method has a better efficiency. Meanwhile, the aerodynamic heating environment of the hypersonic boost glide vehicle was also calculated along the flight trajectory, which laid the foundation for design and analysis of the thermal structure.

关 键 词：高超声速飞行器 气动热环境 流场仿真 边界层外缘参数 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]