中文摘要：

合成翅膀静电干扰气动弹性变形通过一个泛泛地联合的方法被分析，在不同飞行态度下面的合成翅膀特征上的效果被介绍。结构的分析和空气动力学的分析通过有限元素方法被执行(女性) 软件 NASTRAN 和计算液体动力学(CFD ) 软件流畅分别地。关联词数据转移和网孔再生过程被使用联合计算结构动力学(CSD ) 和 CFD 的结果。在在不同飞行态度下面的静态的气动弹性变形分析以后，随飞行速度的增加提起增加，这能被看见，增长价值在僵硬、有弹性的翅膀逐渐地扩大。当飞行速度是时，电梯随攻击角度的增加介绍一种线性增长关系 0.4Ma 或 0.6Ma，而是在有弹性的翅膀的非线性的增长当飞行速度是 0.8Ma 时。在气动弹性变形的效果上，当一致时，有飞行速度和攻击角度的增加的变丑增加的最大值，和增长价值与不同攻击角度随飞行速度的增加减少。结果为设计应用程序提供一本参考书。

英文摘要：

Composite wing static aeroelasticity was analyzed through a loosely coupled method and the effects on composite wing characteristics under different flight attitudes were presented. Structural analysis and aerodynamic analysis were carried out through finite element method （FEM） software NASTRAN and computational fluid dynamics （CFD） software FLUENT, respectively. Correlative data transfer and mesh regenerate procedure were applied to couple the results of computational structure dynamics （CSD） and CFD. After static aeroelasticity analysis under different flight attitudes, it can be seen that lift increases with the increase of flight speed and the incremental value enlarges gradually in both rigid and elastic wings. Lift presents a linear increment relationship with the increase of attack angle when the flight speed is 0.4Ma or 0.6Ma, but nonlinear increment in elastic wing when flight speed is 0.8Ma. On the effect of aeroelasticity, the maximum of deformation increases with the increase of flight speed and attack angle, and the incremental value decreases with the increase of flight speed while uniform with different attack angles. The results provide a reference for engineering applications.