To achieve swept-back, variable camber, and torsional deformation of the aircraft′s morphing wing, a rotating re-entry superstructure with adjustable elastic parameters was proposed. The rotational re-entrant metastructure was composed of an inwardly concave octagon rotated 90° and extended ligaments. The wing section was constructed through the spatial topological filling strategy of the extended straight arm ligaments, forming a bone architecture with deformation capability. Based on the Mohrs theory, a theoretical model of the relative elastic modulus and Poissons ratio of the rotational re-entry metastructures along three directions in space was established. The finite element model of the rotational re-entry metastructures were established by ANSYS software, and five rotational re-entry metastructures prototypes were processed by 3D printer technology. The theoretical, simulation and experimental results were compared respectively. The maximum absolute relative error of Poissons ratio along the x, y and z directions is 10.22%, indicating the accuracy of the theoretical model and the simulation model. The effects of geometric parameters on the elastic parameters of metastructures were analyzed, and it is found that the aspect ratio and the structural angle have a great influence on the mechanical parameters of Poissons ratio, which can provide a theoretical basis for the application of morphing wing skeleton of aircraft.