本文首先建立了航天器姿态动力学及运动学方程，该方程具有较强的非线性特性。通过将状态耦合部分作系统干扰项的处理，使原来的非线性模型转化为线性模型加非线性干扰的形式，从而得到了更加简单明了的姿态控制系统的表达式。

在应用滑模变结构原理对系统进行控制器设计时，首先通过二次型最优法求出了最优滑动面，在此基础上，利用自适应滑模控制原理，设计出了合适的系统控制律。

最后，运用所设计的姿态控制系统对某航天器进行数值仿真，并对仿真结果进行了分析。仿真结果很好地体现出所设计的变结构控制器的优点，并成功地对该航天器姿态进行了控制。

-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,