To improve the aerodynamic performance of civil fixed-wing carrier-based UAV, this study presents a variable trailing-edge camber wing design scheme based on a multi-segment drive mechanism. Using the k – ω turbulence model for viscous fluids, comparative aerodynamic analyses across angles of attack are conducted for traditional singlesegment wing structures and 2–5-segment deformable wing structures. Through quantitative evaluation of key parameters such as lift coefficient and lift-to-drag ratio, the 3-segment deformable wing is identified as the optimal aerodynamic configuration. Structural optimization and simulation verification of the wing are carried out based on this scheme. The results show that the kinematic model established for the 3-segment structure achieves precise control of the target deformation angle of 30° through simulation verification, with excellent collaborative motion of each rotating rib and a continuously smooth wing profile without jamming. Finite element strength analysis indicates that the maximum Von-Mises stress in the structure is 287.12 MPa, with a safety margin of 3.81 (based on the yield strength of 1093 MPa for 15–5PH stainless steel), meeting the strength requirements under designed loads. The proposed multi-segment variable trailingedge camber wing design method provides a complete parameter matching and performance verification system for the engineering implementation of high-lift wings in carrier-based UAVs.