南京航空航天大学学报2012，Vol.44Issue(4)：493-496,4.
可变后缘弯度机翼柔性蒙皮的变形特性分析
Deformation of Flexible Skin for Variable Trailing-Edge Camber Wing
摘要
Abstract
The method for calculating the displacement of the flexible skin under the air loads is developed based on the panel method and the finite element method. Numerical results show that the^flexible skin on the upper surface of the trailing edge will bubble under the air loads and the bubble has a great effect on the aerodynamic pressure near the surface of the local deformation. Then, the relationships between the deformation of flexible skin and its parameters such as elastic modulus, thickness and pre-strain are discussed. It can be seen that the displacement of flexible skin firstly increases and then decreases with the increasing flap angle of trailing edge. To increase the skin thickness can reduce the minimum elastic modulus and the minimum tensile stiffness. But the skin thickness is limited by the space of wing structure. The minimum tensile stiffness based on the Jacobs rules will reduce with the increasing pre-strain acting in the flexible skin.关键词
飞行器设计/可变后缘弯度/柔性蒙皮/弹性模量/蒙皮厚度/预应变Key words
aircraft design/ variable camber of trailing edge/ flexible skin/ elastic modulus, thickness of flexible skin/ pre-strain分类
航空航天引用本文复制引用
尹维龙,田东奎..可变后缘弯度机翼柔性蒙皮的变形特性分析[J].南京航空航天大学学报,2012,44(4):493-496,4.基金项目
高等学校博士学科点专项科研基金(20102302120032)资助项目 （20102302120032）
中央高校基本科研业务费专项基金(HIT.NSRIF.2012028)资助项目 （HIT.NSRIF.2012028）
特种环境复合材料技术重点实验室开放基金资助项目. （）
