刚性隔热瓦瞬态热传导及影响研究  

Research and analysis of transient heat transfer on the rigid ceramic tile

作　　者：董永朋[1,2] 辛健强[2] 徐腾飞[2] 屈强[2] 洪文虎[2] DONG Yongpeng;XIN Jianqiang;XU Tengfei;QU Qiang;HONG Wenhu(Northwestern Polytechnical University,Xi＇an 710072,China;Research and Development Center,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]西北工业大学,西安710072 [2]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《强度与环境》2018年第4期54-59,共6页Structure & Environment Engineering

基　　金：国家自然科学基金(11572353;51572298;11502306);航天先进制造联合基金(U1537204)

摘　　要：针对高超声速飞行器中广泛使用的刚性隔热瓦热防护设计方案,采用Ansysworkbench有限元分析软件,建立了刚性隔热瓦有限元模型,通过瞬态热传导求解器,开展相应的温度场分析,获得了刚性隔热瓦热防护内表面温度随时间的变化历程。进一步,针对影响刚性隔热瓦热防护内表面温度的关键因素,如缝隙宽度、表面辐射率、热导率和材料密度等,开展了相应的影响规律研究,为高超声速飞行器热防护方案设计提供一定的参考。The rigid ceramic tile which was extensively applied to the thermal protect system（TPS） of hypersonic vehicle was investigated on the paper. The finite element software ansysworkbench was used for establishing the finite element model（FEM） to simulate the transient heat transfer on the rigid ceramic tile. The temperature field was obtained through employing the transient heat transfer solver of ansysworkbench. The inner temperature–time-variation of the rigid ceramic tile was plotted. Furthermore, Different temperature distribution numerical results by different parameters that were the width of gap, radiation coefficient, conductivity and density of material were compared to show the influence on the rigid ceramic tile. The paper was beneficial for the rigid ceramic tile design of TPS for the hypersonic vehicle.

关 键 词：刚性隔热瓦 热防护系统 瞬态热传导 影响研究 

分 类 号：V416.4[航空宇航科学与技术—航空宇航推进理论与工程]