Abstract: The test system design of fuselage panel subjected to combined load is an important technology for aircraft structure strength research. A new test system is proposed based on the structure characteristics and load behaviors of fuselage panel. Load separate technic, load center concomitance move technic, tension/compression load horizontal move technic, load assembly equation technic and weight move deduct technique are used on the system. The test system can apply eleven kinds of load cases and about 400t load rank. The test system is adopted on shear stability test of a civil aircraft panel and can meet the development needs of large aircraft.