临近空间高超声速飞行器表面非规则缝隙流动及传热特性研究  

Simulation of Irregular Slot Flow and Heat Transfer Characteristics on Surface of Near Space Hypersonic Vehicle

作　　者：许啸 张军[2] 沈屹 王学德[3] 谭俊杰[3] 张召明[2] Xu Xiao;Zhang Jun;Shen Yi;Wang Xuede;Tan Junjie;Zhang Zhaoming(Zhangjiagang Campus,Jiangsu University of Science and Technology,Suzhou 215600,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]江苏科技大学张家港校区,苏州215600 [2]南京航空航天大学航空学院,南京210016 [3]南京理工大学能源与动力工程学院,南京210094

出　　处：《航空工程进展》2019年第5期707-713,共7页Advances in Aeronautical Science and Engineering

基　　金：江苏省高等学校自然科学研究面上项目(18KJB130002);2018年度一院高校联合创新基金

摘　　要：高超声速飞行器表面的缝隙会对其整体的气动传热和烧蚀特性产生重要影响,研究缝隙内部流动与传热机理对高超声速飞行器热防护系统的设计具有重要意义。针对临近空间高超声速飞行器表面缝隙的非规则变形问题,在热流梯度集中处构建倾斜式形变边界,并采用非结构网格DSMC方法对其内部的流动和传热特性进行模拟,分析非规则形变对缝隙内部涡旋流动及传热特性所造成的影响。结果表明:倾斜式非规则变形会同时产生高温引流和加速导流作用,而高温引流会大幅提高缝隙底部的气动热负荷,是缝隙底部热防护的难点问题。The gap on the surface of hypersonic vehicle will be of an important influence on its overall aerodynamic heat transfer and ablation characteristics.It is important to study the flow and heat transfer mechanism in the gap for the design of thermal protection system of hypersonic vehicle.Aiming at the irregular deformation of the surface gap of a hypersonic vehicle near space,an inclined deformation boundary is constructed at the concentration of heat flux gradient,and the flow and heat transfer characteristics in the gap are simulated by the unstructured grid direct simulation Monte Carlo(DSMC)method.The effect of irregular deformation on the vortex flow and heat transfer characteristics in the gap is analyzed.The results show that inclined irregular deformation can produce both high-temperature drainage and accelerated diversion,and high-temperature drainage can greatly increase the aerodynamic heat load at the bottom of the slot,which is a difficult problem of thermal protection at the bottom of the slot.

关 键 词：临近空间 高超声速 非规则缝隙 DSMC 涡旋流动及传热 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]