民用飞机翼身整流罩区域温度场分析研究及影响  

Analysis Study and Effect of Belly Fairing Zone Temperature for Civil Aircraft

作　　者：闫旭东[1] 南国鹏[1] 苏利焱[1] 简夕忠[1] 

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《民用飞机设计与研究》2015年第3期70-72,90,共4页Civil Aircraft Design & Research

摘　　要：现代民用飞机机身结构大量采用复合材料,但因其遇到高温时会变软,耐热性较差,这就对复合材料周围的环境温度提出了新的要求。以某型飞机的空调组件安装区域进行温度场CFD计算,分析了安装区内的高温部件对机身复合材料结构的影响。为了防止机身复合材料被高温部件烫伤,在高温部件的上方安装隔热板同时进行局部通风冷却,并对相应的工况进行CFD计算对比。A large number of composite materials are used in aircraft structure, which could become weak in high temperature condition. A computational fluid dynamics （CFD）, steady state computational model of the aircraft high temperature area was used to investigate and analyzed. Thermal-protective coating and ventilating is used to protect composite material parts from being heated.

关 键 词：复合材料 高温 温度场 冷却 

分 类 号：V245.3[航空宇航科学与技术—飞行器设计]