论文部分内容阅读
充气式机翼的结构刚度由内充气压决定,其颤振特性需要建立静、动力学耦合的分析方法.机翼结构刚度和固有振动特性需要在静力分析基础上计算,进一步计算非定常气动力,从而采用传统的颤振计算方法分析其颤振特性.针对某一充气式机翼采用膜单元建立了有限元模型.在不同内充压条件下,对充气机翼进行了静力分析得到其结构刚度;然后对机翼进行模态计算和颤振分析.研究表明:各阶模态的频率随内充气压的升高而升高;除典型的弯扭模态外,充气机翼的弦向弯曲模态频率较低;充气机翼的颤振形式除常规的弯扭模态耦合外,弦向弯曲模态同样会发生颤振;机翼的临界颤振速度随内充压的变化近似呈分段线性变化;临界颤振模态及耦合分支在一定气压范围内保持不变.
The structural stiffness of inflatable wing is determined by the internal inflation pressure, and its flutter characteristics need to establish a static and dynamic coupling analysis method.Wait structural stiffness and natural vibration characteristics need to be calculated on the basis of static analysis to further calculate unsteady The flutter characteristics are analyzed by the traditional flutter calculation method.Finally, a finite element model is established for a certain inflated wing using membrane elements.A static analysis of the inflated wings is carried out under different internal pressure conditions Its structure stiffness, and then modal calculation and flutter analysis of the wing.Research shows that: the frequency of each mode increases with the increase of internal pressure; in addition to the typical bending and torsion mode, the inflatable wing The chordwise bending mode frequency is low. In addition to the conventional bending and torsional mode coupling, the flutter mode of the inflating wing also produces chattering in the chordwise bending mode. The critical flutter velocity of the wing varies with the filling pressure The approximate linear change is segmented; the critical flutter mode and coupled branches remain unchanged in a certain pressure range.