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大展弦比柔性机翼飞机的气动弹性是当前理论研究的热点,而风洞试验研究则是揭示大变形气动弹性运动机理和验证理论方法的必要手段。该文建立了能够考虑几何非线性特点的大展弦比柔性机翼风洞试验模型结构设计方案。该方案设计结合几何非线性气动弹性理论分析与模型地面试验,在确保分析模型与理论模型一致的基础上,进行了实物模型的气动弹性风洞试验。风洞试验结果表明大展弦比柔性机翼的结构大变形效应对其气动弹性特性产生了一定影响,大变形导致结构水平弯曲模态发生失稳进而降低了模型的颤振速度,与几何非线性气动弹性分析结果一致。试验颤振速度、颤振模态均与理论分析结果吻合,验证了该文几何非线性气动弹性分析方法的准确性。
The aeroelasticity of large aspect ratio flexible wing aircraft is a hot topic in current theoretical research, while wind tunnel test research is the necessary means to reveal the mechanism and verification theory of large deformation aerodynamic motion. In this paper, a structural design of a wind tunnel test model with large aspect ratio flexible wing that can consider geometric nonlinearity is established. Based on the theoretical analysis of geometric nonlinear aeroelasticity and the model ground test, the scheme is designed to test the aeroelastic wind tunnel of the physical model on the basis of ensuring that the analytical model is consistent with the theoretical model. The wind tunnel test results show that the large deformation effect of the large aspect ratio flexible wing has a certain impact on its aeroelastic properties. The large deformation causes the structural horizontal bending mode to destabilize and thus reduces the flutter velocity of the model, Linear aeroelastic analysis of the same. The test flutter velocity and flutter mode agree well with the theoretical analysis, which verifies the accuracy of the proposed method for geometric nonlinear aeroelastic analysis.