The invention discloses a method for controlling the decoupling guidance of a rotary 
missile. The method comprises the following steps that 1) a 
racemization cabin section is arranged between the front cabin section and the rear cabin section of the rotary 
missile; 2) an 
inertia measuring element is installed in the front cabin section, so that an 
accelerometer of the inertial measurement elementand the sensitive axis of a 
gyroscope are parallel to each axis of the front cabin section of the rotary 
missile; 3) the three-axis 
angular velocity data and the acceleration data output by the 
inertia measuring element are collected and calculated through a control plate, and a 
rolling angle value coupled to the front cabin end is obtained; and 4) a motor in the 
racemization cabin section is controlled by calculating the difference between the 
rolling angle of the front cabin section and the set 
rolling angle, so that 
coupling among three channels namely, the 
yaw, pitching and rolling-rotation is reduced to the minimum, wherein the 
racemization cabin comprises a shell, a motor and a bearing are arranged inside the shell, shafts are arranged inside the motor and the bearing, slip rings arearranged inside the shafts, and one ends of the shafts are provided with structural connecting ports of the rear cabin section. And therefore, the problems that 
coupling of the 
yaw and pitching channels is strong in the existing rotary 
missile guidance, and the control is difficult are solved.