空天飞行器变形翼在实现翼展弯曲、扭转及后掠变形时对柔性蒙皮提出面内大变形和面外高承载能力的要求，提出一种具有可调泊松比特性的混合超结构蒙皮结构，由内凹六边形与四角星形胞元构成内部混合超结构，并在两侧粘接柔性表层构成。基于梁理论建立了混合超结构胞元x、y方向相对弹性模量和xy平面泊松比的理论模型，且理论与仿真结果误差不大于10%，验证了理论模型的准确性。研究了胞元几何参数对相对弹性模量和xy平面泊松比的影响，发现胞壁厚度对两者影响最大，其次是水平胞壁长度，四角星形内角对两者影响最小。对超结构面内变形能力进行了参数研究，并对4种不同超结构的比刚度进行了分析，结果表明新型混合超结构在一定胞元内角范围内的比刚度更具优势，研究结果可为高速飞行器变形翼蒙皮的应用提供理论基础。

To satisfy the requirements of in-plane large deformation and out-of-plane high bearing capacity for flexible skin imposed by the morphing wing of aerospace vehicle in realizing continuous variable span-wise bend， span-wise torsion， and sweep， we propose a hybrid metastructure skin structure with tunable Poisson’s ratio. This structure consists of a hybrid metastructure composed of a concave hexagon and a quadrangular star cell， with a flexible surface bonded on both sides. Based on the theory of beam buckling， the theoretical model of the relative elastic modulus in x and y directions and Poisson’s ratio in the xy plane of the hybrid metastructure cell is established. The accuracy of the theoretical model is verified by the relative errors of the theoretical and simulation results which is not greater than 10%. The effects of cell geometry parameters on the relative elastic modulus and Poisson’s ratio in the xy plane are studied. The results show that the thickness of the cell wall exhibits the largest effect on both， followed by the length of the horizontal cell wall， while the inner angle of the quadrangular star has the least effect on both. The in-plane deformation capacity of the metastructure is studied. The comparative analysis of the specific stiffness of four different metastructures shows that the new hybrid metastructure has more advantages in the specific stiffness within a certain range of cell angles. The results provide a theoretical basis for the application of morphing wing skin of high-speed aircraft.