Abstract: The stress state of fuselage panel is very complex, and the test platform can be only used to apply standard loads, such as tensile/compression load, shear load, pressure load or their combination. A load calculation scheme for combined loading test of fuselage panel is introduced in the paper. Firstly, the standard loads ratio is obtained, and the standard loads is combined according to the proportion of each standard loads. The finite element analysis is carried out under the combined loading, and the result is compared with the original finite element analysis result. The axial forces are consistent, and the errors of each strain component are all within 5%. The results show that the load calculation scheme is feasible.