新型零泊松比蜂窝结构力学性能及其驱动方法研究

In order to meet the contradictory requirements of flexibility, stiffness and light weight of the smart morphing structure in the research of morphing aircraft, this proposal studies the mechanical properties and pneumatic driving method of the novel zero Poisson's ratio honeycomb structure. A novel zero Poisson's ratio cellular topology structure is proposed to solve out-of-plane warpage deformation problem of the traditional honeycomb, the geometric nonlinear behavior of the structure is analyzed, and the influence mechanism of the honeycomb geometric parameters on its equivalent elastic modulus, strength and stability is clarified, and its structural optimization design method is also established. The novel zero Poisson's ratio honeycomb structure based on shape memory polymer composite was prepared by Kirigami process to obtain variable stiffness characteristics to solve the contradiction between flexible deformation and rigid bearing of morphing structure. The constitutive model of the shape memory polymer composite is established, and the stiffness variation law of the variable stiffness zero Poisson's ratio honeycomb structure is obtained. A pneumatic distribution driving method of the honeycomb structure is proposed to realize various kinds of active deformation such as in-plane stretching, shearing, out-of-plane bending and torsion of this novel zero Poisson's ratio honeycomb structure. The new zero Poisson's ratio honeycomb structure based on shape memory polymer studied in this proposal will provide a new technical approach for adaptive morphine wing, which has strong theoretical significance and engineering application value.

本项目针对变体飞行器研究中的智能变形结构对柔度、刚度和轻质等方面的矛盾需求，开展新型零泊松比蜂窝结构力学性能及其驱动方法研究。提出一种新型的零泊松比蜂窝拓扑结构，解决传统蜂窝面外翘曲变形问题，综合考虑结构非线性行为，阐明蜂窝几何参数对其等效弹性模量、强度与稳定性的影响机制，完善其结构优化设计方法；采用Kirigami（剪纸）工艺制备以形状记忆聚合物复合材料为基材的该新型零泊松比蜂窝结构，使其获得变刚度特性，以解决变形结构柔性变形和刚性承载的矛盾，同时建立形状记忆聚合物复合材料的本构模型，并得出变刚度零泊松比蜂窝结构的刚度变化规律；提出一种基于气压调节的蜂窝结构分布驱动方法，实现新型零泊松比蜂窝结构的面内伸缩、剪切和面外弯曲、扭转等多种形式的主动变形。本项目所研究的基于形状记忆聚合物的新型零泊松比蜂窝结构将为自适应变形机翼提供新的技术途径，具有较强的理论意义和工程应用价值。

变体飞行器可以通过改变气动外形和结构形状来扩展飞行器的空气动力学飞行包线，提高飞行器燃油效率、机动性和多任务适应能力。目前限制变体飞行器发展的一个关键因素是轻质、变形/承载一体化的材料和结构，变形机翼需要在柔性（执行变形）、刚度（承受和传递气动载荷）和重量（最小化风机重量）之间进行权衡以获得最佳的性能。蜂窝结构因其轻质、大变形和高面外刚度的特点，已经在航空领域得到了广泛应用。本项目针对变体飞行器研究中的自适应变形结构对柔度、刚度和轻质等方面的矛盾需求，开展新型零泊松比蜂窝结构力学性能及其驱动方法研究。提出四角星形零泊松比蜂窝拓扑结构，解决传统蜂窝面外翘曲变形问题，阐明蜂窝几何参数对其等效弹性模量、强度与稳定性的影响机制，并提出结构优化方案；采用Kirigami（剪纸）工艺制备四角星形零泊松比蜂窝结构，使其获得变刚度特性，以解决变形结构柔性变形和刚性承载的矛盾，同时建立形状记忆聚合物的本构模型，得出变刚度零泊松比蜂窝结构的刚度变化规律；提出一种基于气动肌肉的蜂窝结构分布驱动方法，实现三维四角星形零泊松比蜂窝结构的面内伸缩、剪切和面外弯曲、扭转等多种形式的主动变形。本项目所研究的新型零泊松比蜂窝结构将为自适应变形机翼提供新的技术途径，具有较强的理论意义和工程应用价值。