| 航空结构声激励应力的仿真研究 |
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| 引用本文： | 吴晓明,盛元生,沙云东,王克明.航空结构声激励应力的仿真研究[J].数学的实践与认识,2005,35(4):101-104. |
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| 作者姓名： | 吴晓明 盛元生 沙云东 王克明 |
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| 作者单位： | 1. 沈阳航空工业学院理学系,辽宁,沈阳,110034
2. 沈阳航空工业学院动力系,辽宁,沈阳,110034 |
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| 基金项目： | 航空科学基金资助项目 (99B5 40 0 7) |
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| 摘 要： | 利用回归分析方法,建立声激励下飞机襟翼振动总加速度和总应力对总声压的仿真模型,及总应力对振动总加速度的仿真模型.通过模式识别,得到结构应力响应与加速度线性和非线性关系的界限,以及结构应力响应、结构加速度响应与总声压线性和非线性关系的界限.
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| 关 键 词： | 声激励 应力响应 仿真模型 模式识别 |
| 修稿时间： | 2004年2月15日 |
A Simulation study of Stress of Aircraft Structures Subjected to Acoustic Excitation |
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| WU Xiao-ming,SHENG Yuan-sheng,SHA Yun-dong,WANG Ke-ming.A Simulation study of Stress of Aircraft Structures Subjected to Acoustic Excitation[J].Mathematics in Practice and Theory,2005,35(4):101-104. |
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| Authors: | WU Xiao-ming SHENG Yuan-sheng SHA Yun-dong WANG Ke-ming |
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| Institution: | WU Xiao-ming1,SHENG Yuan-sheng2,SHA Yun-dong2,WANG Ke-ming2 |
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| Abstract: | By employing regression analysis, the simulation models of total vibration acceleration and total stresses with respect to total sound pressure as well as the simulation models of total stresses with respect to total vibration acceleration of an aircraft flap under acoustic excitation were given. The limitation of the linear and non-linear relationships of the structural stress response to the total acceleration response as well as that of the structural stress response and structural acceleration response to the total sound pressure were obtained via pattern recognition. |
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| Keywords: | acoustic excitation stress response simulation model pattern recognition |
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