| 邵闯*,葛森.层合板结构元件动态S-N曲线的测定方法[J].实验力学,2009,24(3):264~268 |
| 层合板结构元件动态S-N曲线的测定方法 |
| Dynamic S-N Curve Measurement for Laminated Composite Components |
| 投稿时间：2008-12-04 修订日期：2009-02-24 |
| DOI： |
| 中文关键词: 层合板 元件 振动疲劳 均方根应变 测试 |
| 英文关键词:laminated panel component vibration fatigue root square means |
| 基金项目: |
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| 中文摘要: |
| 在确定了飞机壁板结构的动力学特性后，为预计其声疲劳寿命，传统的方法必须采用飞机壁板结构的典型结构件并通过高声强行波管试验获得这种结构的声疲劳S-N曲线。为减少试验时间和费用，利用振动台获取典型层合复合材料结构元件的振动S-N曲线以代替声疲劳S-N曲线。根据典型复合材料的飞机蒙皮壁板结构形式，利用加筋复合材料层合板设计了用于振动试验的两种结构形式的梁元件。为获得准确的试验结果，试件模拟了实际的连接形式，并用于得到εrms-N振动试验中。所有试件的试验采用相同的振动激励谱形，并在不同的随机振动量级进行试验，利用最小二乘法拟合得到的εrms-N数据。这种测试方法可用于飞机结构抗声疲劳设计的实践中。 |
| 英文摘要: |
| After the dynamic characters of aircraft reinforce-skin structure are determined, in order to predict the sonic fatigue life of this structure, conventional Progressive Wave Tube test with high acoustic intensity is necessary to get sonic fatigue life S-N curve for the typical aircraft structure. In order to reduce the test cost and timesaving, vibration shaker and laminated composite components of typical aircraft structure were designed and used to get the vibration S-N curve for the structure instead of sonic fatigue S-N curve. According to typical aircraft structure, two kinds of beam specimens made of laminated composite panel were designed. Simulated specimen shapes of various practical joint configurations were adapted in order to get the accurate results and were used in vibration fatigue test to get ε-N curves. All beam specimen tests used the same shape of narrowband spectrum and carried out based on several random vibration loads. ε-N curves was obtained by fitting vibration fatigue test results. This measurement can be used in anti-sonic fatigue design for aircraft structure. |
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