PURPOSE: To provide a highly maneuverable missile capable of generating a high maneuvering acceleration even upon flying with a low speed by deviating a propulsive force without any loss of the propulsive force by a method wherein the steering wings of the missile are provided with auxiliary propulsive devices or auxiliary propulsive nozzles to steer the steering wings in the same manner as aeronautical steering under the combustion of a main propulsive device.

CONSTITUTION: The title missile is provided with auxiliary propulsive devices 3 on steering wings 2 and auxiliary propulsive nozzles 13 on steering wings 12 as well as an auto-pilot switching device 5, switching auto-pilot operating devices 7, 8 effecting the control of propulsive charge 9 during the combustion and after the combustion of the propulsive charge 9, whereby necessary maneuvering acceleration, given by a target detecting device 4, can be obtained by propulsive force deviating method during the combustion of propulsive charge and by aeronautical method after the combustion of the same charge. In this case, a control system is required to provide the steering wings with a steering command only same as the control system so far and, therefore, any special actuator for deviating the propulsive force like as so far is not necessitated and the loss of a thrust after deviating the propulsive force can be eliminated.