Influence of vibration amplitude on motion-induced aerodynamic force of a streamline box girder
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摘要: 研究了强迫振动振幅对流线型箱梁断面自激气动力的影响。采用1:70的刚性节段模型开展了测压试验，获得了不同迎角的模型断面在不同振幅下的气动压力和分布，探讨了气动力特性。试验中的扭转振幅范围为2°~16°，竖向振幅范围为5~23mm，来流迎角分别为0°和±5°。测试结果表明，在迎角α=0°条件下，当扭转振幅At ≤8°，或竖向约化振幅Av/D≤0.46时，自激气动力的线性谐波占整体气动力的比例在95%以上，没有明显的高次谐波分量。当扭转振幅At > 8°，来流迎角为+5°时，自激气动力的线性谐波比例可降低到75%，高次谐波的比例可达到25%。扭转振幅对颤振导数A2*、A3*、H2*均存在显著的影响，但竖向振幅仅对H4*存在一定的影响。由此得出，尽管颤振导数随振幅的改变是非线性的，但在一定条件下（如8°扭转角以内），气动力本身不含有明显的高次谐波分量。Abstract: The influence of the vibration amplitude on the motion-induced aerodynamic force of the streamline box girder has been studied. Based on a 1:70 rigid sectional model and electronic pressure scanner valves, the aerodynamic force of the model has been obtained by wind tunnel tests. The range of the torsional amplitude is from 2° to 16°, the range of the vertical amplitude is from 5mm to 23mm, and the angles of attack are 0° and ±5°. At 0° angle of attack, when the torsional amplitude is less than 8° and the vertical reduced amplitude is less than 0.46, the proportions of the linear motion-induced aerodynamic force remain stable and are more than 95%. When the amplitude of the torsional vibration is greater than 8° and the angle of attack is +5°, the linear harmonic components decrease and the high-order harmonic ones increase with the increase of the amplitude. The change of flutter derivatives shows that the torsional amplitude affects A2*, A3* and H2* dramatically, which implies the nonlinear change of the aerodynamic force. However, the vertical amplitude only affects H4*, which is not the control parameter of flutter analysis, and has no influence on the other flutter derivatives. The brief conclusion is that although the force-amplitude behavior of a streamline box girder is nonlinear, there is no obvious high-order component in the motion-induced aerodynamic force under a certain amplitude, especially under 8° torsional amplitude.
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图 1 强迫振动法测压风洞试验
Figure 1. Wind tunnel measuring pressure test based on forced vibration method
图 4 升力、力矩和位移时程曲线(α=0°, At=2°)
Figure 4. History of lift/moment/displacement(α=0°, At=2°)
图 5 单自由度扭转振动中自激气动力频谱
Figure 5. Frequency spectrum of motion-induced aerodynamic force in single-freedom torsional vibration
图 6 单自由度扭转振动中自激气动力基波幅值比例
注:“黑色阴影”代表升力,“斜划线”代表力矩
Figure 6. First harmonic amplitude proportion of self-excited force in single-freedom torsional vibration
图 7 单自由度竖向振动中自激气动力频谱分析
Figure 7. Frequency spectrum of motion-induced aerodynamic force in single-freedom vertical vibration
图 8 单自由度竖向振动中模型自激气动力基波幅值比例
注:“黑色阴影”代表升力,“斜划线”代表力矩
Figure 8. First harmonic amplitude proportion of motion-induced aerodynamic force in single-freedom vertical vibration
图 9 单自由度振动中自激气动力曲线拟合
Figure 9. Fitting curve of motion-induced aerodynamic force in single-freedom torsional vibration
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