The test technology of fuselage panel subjected to combined load is an important technique for aircraft structure strength research. Based on the bearing characteristics and mechanical model of fuselage panel, combined with the research status at home and abroad, through the internal pressure-tensile-shear load test research and the internal pressure-compression-shear load test research, the combined load test technology of fuselage panel has been completed, and the combined load test device for fuselage panels has been developed. The test research breaks through seven key technologies, such as the boundary condition simulation of fuselage panel, applying shear load without transition section, double axial and double frame arrangement, load separation, load center follow-up loading, tension-compression horizontal motion loading, follow-up weight deduction. The test device can apply tensile load 4 000 kN, compression load 4 000 kN,shear load 3 750 kN·m and internal pressure load 0.15 MPa. The test device can complete 11 kinds load case test, the length of the piece is 4 200 mm and the chord length is 3 100 mm. The test device can meet the needs of structure selection test and structure verification test of large aircraft in China.