To study the influence of positive and cosine control canard on the aerodynamic characteristics of rotating missile, the nested grid method is used to simulate the missile rotation and the deflection of the canard in CFD software. Based on the comparison with the wind tunnel test results and the verification of the accuracy of numerical simulation, numerical simulation was carried out on the aerodynamic characteristics of the rotating missile with positive and cosine control modes at different speeds, angles of attack and Mach numbers, and the following conclusions were drawn: When the same maximum canard deflection angle is used, the normal force coefficient of the missile is smaller than that of the static condition, while the lateral force coefficient and lateral moment coefficient are larger than that of the static condition. The lateral moment coefficient of the missile under the control of sines and cosines is smaller than that under the control of no control. The variation of rotational speed has relatively little effect on the normal force, lateral force and the normal force provided by the canard. The lateral force coefficient and lateral moment coefficient of the missile under subsonic condition are larger than those under supersonic condition. During the coning motion of the missile, the changes of the synthetic angle of attack Г have little effect on the periodic average lift coefficient and the lateral force coefficient, and the greater the Г makes the periodic average yaw force coefficient increase. The rotation effect is the reason for the lateral force of the rotating missile with positive and cosine control mode, and the lateral force of the canard and tail is dominant.