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| 大展弦比机翼几何非线性气动弹性响应分析 |
| Analysis of Geometric Nonlinear Aeroelastic Responses of High Aspect Ratio |
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| DOI： |
| 中文关键词: 几何非线性 大展弦比机翼 紧耦合 有理函数拟合 气动弹性响应 极限环 |
| 英文关键词: geometric nonlinearity high aspect ratio wing tight coupling rational function approximation nonlinear aeroelastic response limit cycle oscillation |
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| 中文摘要: |
| 采用UL格式,建立一种适用于结构大变形问题的高精度非线性动响应求解器;通过有理函数拟合,将频域气动力转化为时域下的气动力格式,以紧耦合的方式建立起结构-气动耦合关系.以某大展弦比机翼为例,进行气动弹性响应计算并做颤振分析,可准确预测临界颤振速度;几何非线性对气动弹性响应特性具有显著的影响. |
| 英文摘要: |
| Based on updated Lagrange(UL) scheme,a structural solver with high precision for computation of nonlinear dynamic response of the structure with large deflation was established;In order to express aerodynamic forces in time domain,the aerodynamic matrices are approximated as rational functions via fitting method.Structure- aerodynamic coupling relationship is established in a tight coupling manner.The nonlinear aeroelastic responses of a high aspect ratio wing was calculated by the method presented in this paper,via flutter analysis,it is showed that the method developed in this paper is able to predict accurate critical flutter speed;the geometric nonlinearity makes a significant impact on the aeroelastic responses. |
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