The paper proposes an algorithm for designing a power set of the low-aspect lifting plane for the air-to-air short-range unmanned aerial vehicle. The work objective was to reduce the lifting plane mass and to increase its strength characteristics taking into account the operational loads. The algorithm was based on introduction of the topological optimization method in terms of calculating the structure maximum static stiffness under constraints in volume. Calculations of the stress-strain state and topological optimization were carried out using the ANSYS Workbench 19.2 software package. Boundary conditions were determined; load acting on the wing was set. Material suitable for manufacturing the structure using additive technologies was selected for optimization. Topological optimization resulted in obtaining a structural power diagram of the wing power frame. Taking into account the actual operating conditions, a skin of constant thickness was added to the resulting load-bearing frame. To verify the study, comparative analysis of the optimized wing model and its possible analogue made by traditional methods was carried out. Results of this analysis showed that the mass of the optimized lifting plane was by 12.7% less compared to the mass of a typical stamped structure. At the same time, the maximum equivalent stress values for the optimized wing were 755.7 MPa, which was by 10.3% less than for the standard design. Recommendations were given for further stages of designing the resulting lifting plane.