paper first established the spacecraft attitude dynamics and kinematics equation, the equation has strong nonlinear characteristics. By coupling part of the state system for the disturbance, so the original nonlinear model into a linear model nonlinear increases in the form of interference, and thus a more straightforward attitude control system expression. The application SMVSC tenets of the system controller design, the first through the quadratic optimal method, the optimal sliding surface, on this basis, using adaptive sliding control theory and design a suitable system control law. Finally, using the design of the attitude control system for a spacecraft numerical simulation, and simulation results are analyzed. Simulation results reflect good design of variable structure controller,

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