Error Quaternion and Its Application of Attitude Control for a Spacecraft

In this paper,the quaternion is taken for positional parameters to control the attitude of a spacecraft.First,a variation-the error quaternion vector can be attained.The non-single question of the end-attitude of the spacecraft can be solved.Second,the method of non-liner three-axis attitude controls is presented by a typical example,which uses the error quaternion as feedback and control moment gyros as a primary actuating device,and introduces Lyapunov functions to control the non-linear system.It is a new methodology for large spacecraft attitude control.Comparing with Euler's method,the method issued in this paper is much faster and higher precision