As a key part of unmanned aerial vehicles （UAVs）， the structural design of wings has an important effect on the reliability of UAVs. A small thickness， high sweepback and high-bearing composite wing with single-closed room and rectangular beam is designed to meet the requirements of high speed and large maneuvering UAVs. The finite element model of the designed wing is established in ANSYS software. The strength analysis of metal and composite structure in the wing is carried out using von-Mises criterion and Tsai-Wu criterion， respectively. The reliability of structure design and the accuracy of finite element model are verified by the static experiment. The results show that the simulation results have good agreement with the experimental data， and the error of displacement and strain is within the allowable range. The experimental results show that composite wing with single-closed room and rectangular beam has good technology， high bearing capacity and good symmetry. Its strength， stiffness and ratio of load to weight are beyond the traditional wing， which provides a reference for the structural design of higher performance composite wings.