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.