高超声速进气道前缘流场-热-结构耦合分析  

Fluid-thermal-structural coupling analysis on leading edge of hypersonic inlets

作　　者：张胜涛[1,2] 陈方[1] 刘洪[1] 

机构地区：[1]上海交通大学,上海200240 [2]中国航发商用航空发动机有限责任公司,上海200241

出　　处：《空气动力学学报》2017年第3期436-443,共8页Acta Aerodynamica Sinica

基　　金：国家自然科学基金项目(11102111;11672183;91641129)

摘　　要：通过分析高超声速流场-热-结构耦合问题的机理过程,对多场耦合模型进行了数学物理描述,以此发展了松耦合分析策略框架。在此基础上,采用自适应耦合计算时间步长、混合插值策略和复杂外形网格变形等方法,实现了多场耦合分析平台。针对高超声速飞行器进气道前缘结构的耦合特征进行了初步分析研究,计算结果揭示了在持续长时间飞行条件下流场-热-结构耦合的时空分布特征,为深入开展高超声速飞行器热防护系统的综合性能评估及优化提供了理论与技术支撑。By analyzing the mechanism of hypersonic fluid-thermal-structural coupling problem, a multi-field coupling model was described mathematically and physically, and a loose coupling analysis strategy framework was developed. On the basis of this framework, a multi- field coupling analysis platform was realized by using adaptive coupling step-size, hybrid interpolation strategy, and mesh deformation method for complex configuration. A preliminary analysis was conducted on the coupling characteristics of the leading edge of hypersonic vehicle inlets. The calculated results reveal the temporal-spatial characteristics of the fluid-thermal- structural coupling problem in long-time aeroheating environments, and provide theoretical and technical support for the comprehensive performance evaluation and optimization of the thermal protection system of hypersonic vehicles.

关 键 词：高超声速流动 进气道 流场-热-结构耦合 热防护 自适应耦合步长 耦合策略 激波相互作用 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]