| 飞机襟翼声疲劳应力的仿真与模式识别 |
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| 引用本文： | 吴晓明,盛元生,沙云东,王克明,秦政棋,李宴喜.飞机襟翼声疲劳应力的仿真与模式识别[J].沈阳航空工业学院学报,2004,21(2):1-4. |
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| 作者姓名： | 吴晓明 盛元生 沙云东 王克明 秦政棋 李宴喜 |
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| 作者单位： | 沈阳航空工业学院,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、结构加速度响应与总声压线性和非线性关系的界限，以及结构应力响应与加速度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 |
| 文章编号： | 1007-1385(2004)02-0001-04 |
| 修稿时间： | 2003年9月3日 |
Sonic fatigue stress simulation and pattern recognition of an aircraft flap |
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| WU Xiaoming,SHENG Yuansheng,SHA Yundong,WANG Keming,QIN Zhengqi,LI Yanxi.Sonic fatigue stress simulation and pattern recognition of an aircraft flap[J].Journal of Shenyang Institute of Aeronautical Engineering,2004,21(2):1-4. |
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| Authors: | WU Xiaoming SHENG Yuansheng SHA Yundong WANG Keming QIN Zhengqi LI Yanxi |
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| Abstract: | Employing regression analysis ,the simulation models of aggregate vibration acceleration and aggregate stresses with respect to aggregate sound pressure as well as the simulation models of aggregate stresses with respect to aggregate 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 and structural acceleration response to the aggregate sound pressure as well as that of the structural stress response to the aggregate acceleration response were obtained via pattern recognition. |
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| Keywords: | Acoustic excitation stresses response simulation model pattern recognition |
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