论文部分内容阅读
建立了柔性蒙皮在气动载荷作用下的变形分析方法.翼型压力分布计算采用面元法,结构分析采用有限元方法.在此基础上,计算了柔性蒙皮在气动载荷作用下的变形情况以及变形对气动力的影响.数值结果表明:后缘部分的柔性蒙皮在气动载荷作用下被“吸”成鼓包形状;同时,翼型上表面压力在“鼓包”位置出现比较大的变化.采用Jacobs的蒙皮形变准则(蒙皮的最大形变量小于弦长的0.1%),计算和分析了可变形后缘弯度机翼对柔性蒙皮的刚度要求.计算结果表明:对于可变后缘弯度机翼而言,增大蒙皮弯曲刚度和拉伸刚度的比值可以减小蒙皮结构对拉伸刚度的要求.柔性蒙皮的最大形变量是随着其拉伸刚度的降低而增加,但增加的幅度取决于蒙皮弯曲刚度的大小;当蒙皮弯曲刚度大于某个值时,蒙皮的变形量由弯曲刚度来控制,拉伸刚度不在起作用,这对柔性蒙皮的结构设计具有重要的指导意义.
The deformation analysis method of the flexible skin under the aerodynamic load is established.The plane pressure method is used to calculate the airfoil pressure distribution and the finite element method is used to analyze the structure.And the deformation of the flexible skin under the aerodynamic load is calculated And the effect of deformation on the aerodynamics are also discussed.The numerical results show that the flexible skin at the trailing edge is “sucked” into the shape of the bulge under aerodynamic loading, while the pressure on the upper surface of the airfoil appears at the position of “bulge” The Jacobian skin deformation criterion (the maximum skin deformation less than 0.1% of the chord length) is calculated and analyzed, and the stiffness requirements of the flexible skin by the trapezoid camber wing are calculated and analyzed.The calculation results show that for the As for the variable trailing camber wing, increasing the ratio of bending stiffness and tensile stiffness of the skin can reduce the requirement of the skin stiffness on the tensile stiffness.The maximum deformation of the flexible skin is as a function of its tensile stiffness But the increase depends on the bending stiffness of the skin; when the skin bending stiffness is greater than a certain value, the deformation of the skin is controlled by the bending stiffness and the tensile stiffness is not effective, Skin structure design There are important guiding significance.