| For deformable aircraft to achieve large changes in wing sweep angle, area, and leading and trailing edge curvature, the wing skin should have smooth aerodynamic shape, large deformation, high load-bearing capacity and small driving force. Aiming at the demand of flexible skin, a new zero possion’s ratio honeycomb structure is designed by topology optimization method, and the performance of the structure is verified by finite element analysis compared with U-type honeycomb structure and cosine honeycomb structure. The deformation capacity of three structures is compared with the maximum strain of 2%. The tensile deformation of the new honeycomb structure is up to 75%, which is 1.7 times that of U-type honeycomb structure and 2.1 times that of cosine honeycomb structure. The new honeycomb structure has strong deformability. When the maximum displacement is the same, the required driving force is 0.51 times and 0.28 times of the U-shaped honeycomb structure and the cosine-shaped honeycomb structure respectively. The new honeycomb structure has high load-bearing capacity. When the rubber skin of the honeycomb structure is under the same pressure load and in the initial unstretched state or stretched state, the maximum normal displacement of the new honeycomb structure skin is small, which is 0.4 times or 0.56 times that of U-type honeycomb structure skin, 0.29 times or 0.42 times that of cosine honeycomb structure skin. In addition, by appropriately increasing the wall thickness, the bending resistance of the new honeycomb structure can be significantly improved. Analysis results show that the new honeycomb structure designed in this paper has the advantages of large deformation, high load-bearing capacity and low driving force.