蒙皮蜂窝芯板结构的稳定性分析与优化设计

发布时间：2018-05-17 21:09

本文选题：蜂窝芯结构 + 稳定性分析　；参考：《中国科学技术大学》2015年硕士论文

【摘要】：在当今航空、航天领域研究中,飞行器的智能变体技术是研究热点,同时因其结构特性以及适应飞行环境的苛刻需求,也使得智能变体技术的研究成为技术难点。从早期的“类鱼鳞状叠片式”传统刚性蒙皮到现今的复合材料蒙皮结构,蒙皮的变形技术正在向应用智能复合材料结构的方向演进。随着蜂窝复合夹层结构材料在生产和生活中的广泛应用,其结构自身的优良特性表现的越来越突出。在上述的大背景下,本实验课题组将蜂窝夹层结构引入到变体飞行器的蒙皮结构设计,同时引入柔性机构的理念。通过分析蜂窝夹芯结构的拓扑构型和尺寸参数对自身结构性能的影响规律,以期得到其应用于超弹性蒙皮结构变形时,其对蒙皮气动性能的影响规律。本文系统地分析了蜂窝夹芯板结构的国内外研究现状和发展趋势,对蜂窝夹芯板结构的力学性能及稳定性进行初步研究。以应用于变体飞行器蒙皮结构设计中的蜂窝芯结构为研究对象,在经典的Gibson公式和Euler梁理论的基础上,在满足机翼实现连续变体所需的低共面模量和高异面刚度的基础上,建立柔性蜂窝芯结构的参数优化模型。借助智能算法对特定蜂窝芯单元选型参数进行多目标优化设计,得到了不同蜂窝芯结构的选型参数对各自面内变形能力的影响规律,进行蒙皮蜂窝芯结构的选型分析,并开展了蜂窝芯板结构的变形驱动方案设计。本文的主要内容如下： 1.对自适应机翼技术、蜂窝复合材料的国内外研究现状进行了介绍和总结,阐述了论文的来源及研究意义。 2.对蜂窝夹层结构的自由振动及稳定性进行了分析,得出了芯板结构的弯曲平衡方程和屈曲基本方程。 3.在满足机翼实现连续变体所需的低共面模量和高异面刚度的基础上,确定柔性蜂窝芯结构的参数优化模型的边界条件及其相应目标函数,得到蜂窝芯结构参数优化数学模型。 4.借助遗传算法对特定蜂窝芯单元选型参数进行多目标优化设计,得到了不同蜂窝芯结构的选型参数对面内变形能力的影响规律,并进行蒙皮蜂窝芯结构的选型分析。 5.基于理论和优化仿真研究,开展了对柔性蜂窝芯弹性蒙皮的结构设计,提出了基于正、负泊松比蜂窝芯板组合的机翼蒙皮结构驱动设计方案。
[Abstract]:In the field of aeronautics and spaceflight, the intelligent variant technology of aircraft is a hot research topic. At the same time, due to its structural characteristics and harsh requirements to adapt to the flight environment, the research of intelligent variant technology has become a technical difficulty. From the early "fish-like laminated" traditional rigid skin to the present composite skin structure, the deformation technology of the skin is evolving towards the application of intelligent composite structure. With the wide application of honeycomb sandwich materials in production and daily life, the excellent properties of honeycomb sandwich structures are becoming more and more outstanding. Under the above background, the honeycomb sandwich structure is introduced into the design of the skin structure of the variant aircraft, and the concept of flexible mechanism is introduced at the same time. By analyzing the influence of the structure parameters and topological configuration of honeycomb sandwich structure on the structural properties of honeycomb sandwich structure, the effect of the structure on the aerodynamic performance of the skin is obtained when it is applied to the deformation of the superelastic skin structure. In this paper, the present situation and development trend of honeycomb sandwich panel structure at home and abroad are systematically analyzed, and the mechanical properties and stability of honeycomb sandwich panel structure are studied preliminarily. Based on the classical Gibson formula and the Euler beam theory, the honeycomb core structure used in the design of the skin structure of the variant aircraft is studied. On the basis of satisfying the low coplanar modulus and the high cross-plane stiffness required for the wing to realize the continuous variant, the honeycomb core structure is studied. The parameter optimization model of flexible honeycomb core structure is established. With the help of intelligent algorithm, the multi-objective optimization design of the selection parameters of specific honeycomb core units is carried out, and the influence of the selection parameters of different honeycomb core structures on their in-plane deformation capacity is obtained, and the selection and analysis of the skin honeycomb core structures are carried out. The deformation-driven scheme of honeycomb core board structure is designed. The main contents of this paper are as follows: 1. The research status of adaptive wing technology and honeycomb composite materials at home and abroad are introduced and summarized. The origin and significance of this paper are described. 2. The free vibration and stability of honeycomb sandwich structure are analyzed. The bending equilibrium equation and buckling basic equation of core plate structure are obtained. 3. On the basis of satisfying the low coplanar modulus and high cross-plane stiffness of the wing to realize the continuous variation, the boundary conditions and the corresponding objective functions of the parameter optimization model of the flexible honeycomb core structure are determined, and the mathematical model of the parameter optimization of the honeycomb core structure is obtained. 4. By means of genetic algorithm, the multi-objective optimization design of specific honeycomb core unit selection parameters is carried out, and the influence law of different honeycomb core selection parameters is obtained, and the selection analysis of skin honeycomb core structure is carried out. 5. Based on the theory and optimization simulation, the structure design of flexible honeycomb core elastic skin was carried out, and the drive scheme of wing skin structure based on the combination of positive and negative Poisson's ratio honeycomb core was proposed.
【学位授予单位】：中国科学技术大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：TB383.4

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