复合材料飞机动力学建模研究  

Research on Dynamic Modeling for Composites Aircraft

作　　者：吕继航 罗琳胤 

机构地区：[1]中航通飞研究院有限公司,珠海519040

出　　处：《航空制造技术》2016年第4期68-71,共4页Aeronautical Manufacturing Technology

摘　　要：在进行复合材料飞机气动弹性、动响应等分析时,需要进行飞机结构动力学建模。为此,基于经典层合板理论进行了复合材料刚度的等效计算,结合结构力学闭剖面理论分析了飞机剖面的弯曲、扭转刚度特性,并根据刚度分布建立了全复合材料飞机的动力学单梁模型。与地面共振试验结果的对比表明,复合材料飞机动力学单梁模型是有效的,且相对板壳模型更接近试验结果。建模方法对复合材料飞机结构设计具有指导意义。To the requirement of aeroelastic and dynamic response analysis, dynamic modeling of composites aircraft is essential. The equivalent stiffness of composites structure is deduced by applying Classical Laminate Theory, bending and torsion stiffness of composites aircraft are calculated base on close section theory of Structural Mechanics, and the single-beam dynamic modeling of composites aircraft is constituted. Compare with Ground Vibration Test results, the single-beam dynamic model of this paper is effective, and it is relatively similar to test results contrast with shell model. It provides significant guidance for the structural design of composites aircraft.

关 键 词：复合材料飞机 刚度等效 动力学建模 

分 类 号：V214[航空宇航科学与技术—航空宇航推进理论与工程]