Abstract: This paper introduces a method to decouple the complex load to the standard loads that can be applied by the test platform. Firstly, the residual function of the original strain components and the strain components of the combined load of the fuselage panel examination area is constructed, the independent variable of the function is the standard loads ratio. Then, this problem is transformed into unconstrained nonlinear programming problem by minimizing the sum of square function. Fminunc function is used to solve the problem, finally the standard loads ratio is got as well as the test loads.