The invention discloses a spacecraft attitude control method based on a variable and inertia flow velocity adjustment controller and an actuating mechanism of the spacecraft attitude control method. The actuating mechanism comprises a main ring liquid filling annular pipe, a main ring pressure pump, an oil storage tank, a valve, a main ring liquid outlet connecting pipe, a main ring liquid return connecting pipe, a variable ring liquid filling annular pipe, a variable ring pressure pump, a variable ring liquid outlet connecting pipe, a variable ring liquid return connecting pipe and a control mechanism. A flowing loop is formed by the main ring liquid filling annular pipe, the main ring pressure pump, the oil storage tank, the valve, the main ring liquid outlet connecting pipe and the main ring liquid return connecting pipe. The other flowing loop is formed by the variable ring liquid filling annular pipe, the variable ring pressure pump, the oil storage tank, the valve, the variable ring liquid outlet connecting pipe and the variable ring liquid return connecting pipe. According to the spacecraft attitude control method based on the variable and inertia flow velocity adjustment controller and the actuating mechanism of the spacecraft attitude control method, the problems of rotation speed saturation of angular momentum exchange type actuating mechanisms in the process of wide-angle attitude adjustment in the prior art and much mass and the size requirement burden, caused by generated actuating mechanism redundant configuration of a traditional actuating mechanism in order to solve the problem of rotation speed saturation, of a spacecraft are solved.