论文部分内容阅读
变形机翼技术的实现离不开柔性蒙皮技术的支持,提出了一种应用于变形机翼夹心式柔性伸缩蒙皮的面内褶皱型梯形蜂窝蒙皮支撑结构。通过理论分析研究了该支撑结构的面内伸缩特性,得到其面内横向无量纲化等效弹性模量大小与3个参数(形状系数k、宽度系数t和高度系数h)之间的关系:其等效弹性模量随k增大而减小,随t增大而增大,随h增大而减小。利用ANSYS软件对其进行了有限元分析并通过实验对其面内力学特性进行了验证。结果表明:理论分析、有限元结果与实验结果基本吻合。通过选择合适的结构参数,其面内横向等效弹性模量可达到原材料弹性模量的10-4,比同等参数下手风琴式支撑结构的面内横向等效弹性模量更小,变形能力更强。相比传统蒙皮支撑结构,该结构可以减小变形过程中的驱动力与能量消耗,提高柔性蒙皮的变形效率。
Deformation wing technology can not be separated without the support of flexible skin technology, and proposes a kind of in-plane fold-shaped trapezoidal honeycomb skin support structure which is applied to the deformation wing flexible sandwich skin. The in-plane telescoping characteristics of the support structure were studied by theoretical analysis, and the relationship between the dimensionless equivalent elastic modulus and the three parameters (shape factor k, width factor t and height factor h) The equivalent elastic modulus decreases with k increasing, increases with t increasing, decreases with increasing h. ANSYS software was used to carry out finite element analysis and verify its in-plane mechanical properties through experiments. The results show that: the theoretical analysis, the finite element results are basically consistent with the experimental results. By selecting the appropriate structural parameters, the transverse equivalent elastic modulus in the plane can reach 10-4 of the elastic modulus of the raw material, which is smaller than the equivalent transverse elastic modulus of the accordion support structure under the same parameters, and the deformation capability is more Strong. Compared with the traditional skin support structure, the structure can reduce the driving force and energy consumption in the deformation process, and improve the deformation efficiency of the flexible skin.