摘要
复合材料蜂窝夹芯板是应用于飞机部分结构上理想的、效率最高的结构形式之一。本文重点针对不同结构、尺寸参数的蜂窝夹芯板进行试验研究,重点分析试验件在振动载荷作用下的动态响应和疲劳寿命的变化情况,并对试验结果进行分析研究,提出结构形式、尺寸参数对蜂窝夹芯板的疲劳性能影响,为后续工程设计和试验方法提供有效支撑。
Composite honeycomb sandwich panel is one of the ideal and most efficient structural forms for certain aircraft structures.This paper focuses on the experimental study of honeycomb sandwich panels with different parameters.The change of dynamic response and fatigue lifespan of test pieces un der vibration load is an a lyzed emphatically.The structural form and size parameters on the fatigue performanee of honeycomb sandwich panels is proposed after analyzing the test results,which provides effective support for subsequent engineering design and test methods.
作者
杨堃
许绯
燕群
Yang Kun;Xu Fei;Yan Qun(Aircraft Strength Research Institute of China,Xi'an 710065,China)
出处
《飞行器强度研究》
2021年第4期15-20,共6页
Aircraft Strength Research
关键词
蜂窝夹芯板
振动疲劳
动力学响应
试验设计
honeycomb sandwich panels
vibration fatigue
dynamic response
experiment design
