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应用面元法和有限法建立了柔性蒙皮在气动载荷作用下的流固耦合分析方法。数值仿真结果表明:位于变形后缘上表面的柔性蒙皮在气动载荷作用下将被“吸”成鼓包形状,且这个局部变形对翼型后缘部分的压力分布具有很大影响。在此基础上,研究了柔性蒙皮在气动载荷作用下的变形随其弹性模量、厚度和初始预应变的变化规律。可以得出,柔性蒙皮的变形量随着翼型后缘偏角的增加而先增大后减小,并不是随着后缘偏角的增加而增大;增加蒙皮的厚度可以减少柔性蒙皮的最小弹性模量和最小拉伸刚度,但蒙皮的厚度受限于机翼的结构空间;满足Jacobs形变准则的蒙皮最小拉伸刚度随着蒙皮预应变的增加而降低。
The fluid-solid coupling analysis method of flexible skin under aerodynamic loading is established by using the bifurcation method and the finite method. The numerical simulation results show that the flexible skin on the upper surface of the trailing edge will be “sucked” into the shape of the bulge under aerodynamic loading, and this local deformation has a great influence on the pressure distribution in the trailing edge of the airfoil. On this basis, the deformation of the flexible skin with the elastic modulus, the thickness and the initial pre-strain under aerodynamic loading is studied. It can be concluded that the deformation of the flexible skin first increases and then decreases with the increase of the trailing edge of the airfoil, and does not increase with the increase of the trailing edge angle. Increasing the thickness of the skin reduces the flexibility The minimum elastic modulus and the minimum tensile stiffness of the skin, but the thickness of the skin is limited by the structural space of the wing. The minimum tensile stiffness of the skin satisfying the Jacobs deformation criterion decreases with the increase of skin pre-strain.