Abstract: To address the structural design conflict of morphing wing skin cores, which require high out-of-plane load-bearing capacity while maintaining high in-plane compliance, a new zero Poisson’s ratio honeycomb structure is proposed, and its in-plane elastic properties are systematically investigated. The honeycomb architecture consists of three fundamental substructures: curved ligaments, circular ring nodes, and horizontal ligaments. Based on Castigliano's second theorem, dimensionless analytical expressions were derived. Finite element homogenization simulations were conducted in Ansys and validated against standard tensile tests performed on FDM-printed specimens. The triangulation of these three independent approaches established a comprehensive parameter-to-performance mapping. The results demonstrate that the in-plane moduli of the novel zero Poisson's ratio honeycomb structure are sensitive to geometric parameters. The transverse elastic modulus Ex is highly sensitive to the horizontal ligament parameter ξ, increasing by approximately 36% as ξ rises from 0.10 to 0.14. The axial modulus Ey and the equivalent shear modulus Gxy are primarily governed by the curved ligaments, enhancing with increasing wall thickness but diminishing with a larger central angle of the curved ligaments. The deviations among the theoretical, numerical, and experimental results are all below 10%, validating the reliability of the methodologies employed. Under identical relative density conditions, compared with the anti-tetrachiral honeycomb, the new structure demonstrates a remarkable enhancement: its transverse elastic modulus Ex exhibits an approximately 8.8-fold increase, and its shear modulus shows a roughly 20% improvement, while maintaining a near-zero Poisson's ratio. This signifies a significantly improved overall in-plane mechanical performance.