论文部分内容阅读
为研究平尾的颤振特性,根据相似性原理,按照保持质量分布和刚度分布不变的原则,设计制造出某飞机后机身-平尾缩比模型。在不改变主要的承力方式及动力学特征的前提下,建立相应的有限元模型,利用亚音速偶极子网格法计算非定常气动力,V-g法求解颤振行列式,通过有限元软件进行颤振分析。结合实际设计要求,不断对平尾模型操纵刚度、平尾轴直径、摇臂高度等参数进行调整,探索设计参数的改变对颤振速压的影响,为飞机平尾的设计提供参考。
In order to study the flutter characteristics of the flat tail, a fuselage-tail-tail ratio model of an aircraft is designed and manufactured according to the principle of similarity and the principle of keeping the mass distribution and the stiffness distribution unchanged. Under the premise of not changing the main bearing and dynamic characteristics, the corresponding finite element model is established, the unsteady aerodynamic force is calculated by subsonic dipole grid method, Vg method is used to solve the flutter determinant, and finite element software Flutter analysis. Based on the actual design requirements, the parameters such as steering stiffness, the diameter of the tail shaft, and the height of the rocker arm are continuously adjusted to explore the influence of the change of design parameters on the flutter speed and provide a reference for the design of the aircraft tail.