A method for building a variable structure control model of a single-axis wheel-controlled quick attitude maneuvering satellite relates to the technical field of satellite attitude control. The method is used for solving the problems that the conventional variable structure controller is not suitable for a quick maneuvering satellite and the design method of the conventional variable structure controller does not have universality. The method provided by the invention comprises the following steps: solving the required design parameters including a, T, delta, epsilon, K and delta I, wherein the specific meanings of the designed parameters are that a is a parameter of reduction of the input moment amplitude, T is a time constant of an input section inertial element and has the functions of increasing the design degree of freedom of the controller and reducing 'buffeting', delta is a variable for judging whether the moment amplitude is switched or not, epsilon is a parameter for eliminating buffeting, K is the coefficient of an attitude angle in a sliding mode surface and Phi is the saturation value of the attitude angle in the sliding mode surface, and delta I is a parameter for reducing the influence of inertia deflection on an attitude control system. The method is used for building the variable structure control model of the single-axis wheel-controlled quick attitude maneuvering satellite.