Abstract：In order to complete the strength analysis and airworthiness verification of aircraft structure, it is necessary to carry out full-size static strength test of aircraft. For different load condition, the reliability and validity of test result are directly affected by whether the balancing design of test load can reflect the real stress condition of the evaluation area. In the full-size static strength test of aircraft, In ordor to simplify the complex loading scheme.Traditional balance loading is used to ensure the loading is accurate in the asseessment area, while the loading is simplify to some loading points in the non assessment area.In this paper, we find out that to the thin-wall structure like civil aircraft, traditional balacncing load in the non asseessment area have an effect on asseessment area,even if the the non asseement area is far away from the asseement area.Taking a front fuselage serious condition of a large civil aircraft as an example,the load design scheme of full-size static strength test of aircraft is studied based on the FEM model,By comparing the result of FEM analysis under theoretical design load and common test load, the optimized test load balancing scheme is put forward, the optimized blancing load is based on the real load in the condition we choose,and the balancing load in the non asseessment area doesn’t change the balace mode of the aircraft. The calculated results show that the internal force under optimized test load is basically identical with it under theoretical design load. According to the research in this paper, we can conclude that the Saint Venmant principl is inapplicable to the thin-wall structure like civil aircraft, in ordor to achieve the vertification purpose, the balancing load we exert should consistent with the real situation.