Coupled heat transfer and thermo-mechanical behavior of hypersonic cylindrical leading edges
Coupled heat transfer and thermo-mechanical behavior of hypersonic cylindrical leading edges
复制标题
高超声速圆柱形前缘的耦合传热和热机械行为
DOI：
10.1016/j.ijheatmasstransfer.2018.02.037
复制
发表时间：
2018
影响因子：
5.2
通讯作者：
Zhang Shengtao
中科院分区：
文献类型：
--
作者：
Chen Fang;Liu Hong;Zhang Shengtao
高超声速飞行器在高热载荷和高机械载荷下的传热和热力学行为分析至关重要。提出了一种时间自适应松散耦合策略，用于高超声速固有流-热-结构特性的建模和分析。为集成自主开发的高超声速气动热力学求解程序和有限元分析专业软件，开发了高超声速计算耦合动力学框架（HyCCD）。嵌入式自适应时间步法、混合插值策略和网格变形法考虑了耦合变量及其性质。以典型圆柱形前缘为模拟模型，研究了化学不平衡、气动加热时间、飞行轨迹和激波干扰等因素的影响。气动热结构响应的时间自适应松耦合分析为高超声速飞行器流体热结构耦合预测提供了一种可靠、适用和高效的方法。
The analysis of heat transfer and thermo-mechanical behavior is crucial to the leading edge of hypersonic vehicles under high thermal and mechanical loads due to severe aeroheating. The present paper proposes a time-adaptive loosely coupled strategy for the modeling and analysis of hypersonic intrinsic fluid-thermal-structural characteristics. A framework of hypersonic computational coupling dynamics (HyCCD) is developed for integrating an independently developed program solving hypersonic aerothermodynamics and a finite element analysis professional software. The embedded adaptive time-step approach, hybrid interpolation strategy, and grid deformation method have taken into consideration coupling variables and their properties. A typical cylindrical leading edge is considered as the simulation model to study the effects of chemical nonequilibrium, aeroheating duration, flight trajectory, and shock interference. The time-adaptive loosely coupled analysis of aerothermostructural response provides a reliable, applicable and efficient prediction for the fluid thermal-structural coupling of hypersonic vehicles.