某飞行器弹翼颤振分析

Flutter Analysis on Wing of An Aircraft

分析某飞行器弹翼的颤振问题,首先建立弹翼有限元模型,计算弹翼模态,根据试验结果,对模型进行修正;用NASTRAN计算单独弹翼和全弹翼的颤振速度和颤振频率,用偶极子格网法计算亚声速非定常气动力,将模态计算结果插值到气动网格上,编程计算弹翼的颤振速度,并与NASTRAN计算结果对比。分析表明,弹翼在飞行速度范围内不会发生颤振。

The flutter problem of the wing of an aircraft is analyzed.Firstly,the finite element model of the wing is set up and the modes are calculated.The model is adjusted basing on the data of modal tests.Then,the flutter speeds and frequencies of half wing and full wing are calculated by NASTRAN.Finally,the aerodynamic force with doublet lattice method is calculated,with the aerodynamic grids to the structural mode results interpolated.The flutter speeds of the wing are calculated by programs,then the results are compared with those of NASTRAN.The analysis has indicated that the flutter of the wing will not occur in the range of its speed.