New algorithm to attitude control for the space station

In this paper, the quaternion is taken for positional parameters to control attitude of the space station. The first, the system dynamic model, which is expressed in quaternion, is given. The second, the method of non liner three axis attitude control is presented, which use quaternion as feedback, control moment gyros as a primary actuating device and introduce Lyapunov functions to control the non linear system. It is a new methodology for large spacecraft attitude control. Finally, a space station is taken as an example, the attitude control simulation is calculated. Comparing with Euler's method, the method issued in this paper is much faster and higher precision.