The invention provides a novel spinning missile control method taking a spinning missile spin cycle as a control reference. According to the scheme, guide instructions obtained by resolving GPS signals are a pitching equivalent rudder deflection angle and a yaw equivalent rudder deflection angle under a quasi missile body coordinate system, wherein the pitching equivalent rudder deflection angle and the yaw equivalent rudder deflection angle need to be converted into an actual pitching rudder deflection angle and an actual yaw rudder deflection angle under a missile body coordinate system respectively; and when a rudder surface is deflected to a reference position, the actual rudder deflection angles are half of the pi times of the equivalent rudder deflection angles in respective guide instructions, rudder deflection reversing is carried out when the rudder surface is deflected to the reference position, and then a gyroscope preassembling angle is set to realize compensation decoupling on a spinning missile double-channel control system.