民用飞机后机身结构静力试验方案设计  

A Static Test Method for the After Fuselage Structure of Civil Aircraft

作　　者：刘佳[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》2013年第A02期10-12,共3页Civil Aircraft Design & Research

摘　　要：针对某民用飞机后机身结构特点和受载形式,设计了相应的静力试验方案。该方案合理模拟了后机身结构的支持和边界条件,同时对后机身严重载荷情况进行分析处理,实现了飞行载荷和惯性载荷在后机身结构上的施加,顺利完成了大部段复杂结构的静强度试验。试验结果表明,后机身结构能够承受极限载荷,其刚度和强度满足设计要求。According to the after fuselage structure of civil aircraft, a static test method was designed. The sup- port and boundary condition were simulated reasonably . The flight and inertia load were applied by analyzing and redistributing the severe load case. Test results show that the after fuselage structure could bear the limit and ulti- mate load; the after fuselage structure has enough stiffness and strength to satisfy the design requirement.

关 键 词：民用飞机 后机身 静力试验 试验方法 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]