文档介绍：May 11, 2004 DP -7 REACTING FLOW ENVIRONMENTS BRANCH ELORET DECOUPLING FLOW & MATERIAL RESPONSE 解耦流及材料反应? TPS materials not selected at the preliminary design phase – computations should guide this choice 初始设计阶段未选择防热系统材料–计算应引导至此选择? Assume that the surface is non-conducting and can only re-radiate – adiabatic back wall assumption 假设表面无传导性,只有再辐射性–隔热后墙假设? Assume that the surface plete bination of atoms reaching it– conservative assumption because maximum heat release can be expected 假设表面促使到达表面的原子完全重组–保守假设从而得出最大散热? Aerothermal analysis can now be performed with a steady flow assumption at any trajectory point – time discretization 气动热分析只能在稳定流场假设下的任意轨道点进行–时间离散化? Time discretization cannot be too fine for putations – enormous number putations required 时间离散化不太适用于 CFD 计算–需要对大量数据进行计算? Need to supplement putations with engineering methodology of acceptable accuracy – engineering methods are much quicker 需要使用合适精准度的工程学方法补充 CFD 计算–工程学方法更为快速 May 11, 2004 DP -8 REACTING FLOW ENVIRONMENTS BRANCH ELORET ABOUT THIS PRESENTATION 关于此次演示? To demonstrate bination of CFD and engineering methodology in defining aerothermal environments for TPS design 演示为防热设计所定义的气动热环境下的 CFD 与工程学方法的结合? Assumes Earth atmospheric flight – flow medium consists of N2, O2, & products 假设地球大气层飞行–气场至少包含氮气、氧气及其化合物? Does not call out material choices or sizing 不涉及材料选择及大小? Uses X-33 flight vehicle asa case study 使用 X-33 飞行器作为案例研究? The presentation is not prehensive account of various approaches 此演示非多种方法的综合预计? The presentation isa focused one – drawn on the experience ofa small team at NASA Ames Research Center 此次演示为一次集中演示–由 NASA 阿姆斯研究中心一个小组经验绘出 May 11, 2004 DP -9 REACTING FLOW ENVIRONMENTS BRANCH ELORET REQUIREMENTS – CONFIGURATION 要求–结构? Since in-depth conduction is neglected, only the outer surface (outer mold line or OML) definition is required 由于已忽略深度传导性问题,此处只要求对外表(外模线,又称 OML )做出定义? Configuration is usually available in some CAD format 在一些 CAD 公式中可得出结构? Translation of CAD formats is an issue 翻译 CAD 公式是一个问题? CAD fil