PURPOSE: To take a wide range of an attack angle of a missile without limit of a stalling angle of the main wing by providing main wings sliding in the direction of the axis of by missile means of a gas servo type longitudinal driver provided in the body and small wings disposed at the head in a manner that steering angles are variable.

CONSTITUTION: Small wings 4 are steered by a small wing driver 9, and main wings 3 are moved longitudinally at a necessary amount through a main wind longitudinal driver 7 with a gas servo type longitudinal driver 5 according to a control command signal necessary to be generated by a control instructing unit 6. The wings 4 are steered in a state that a missile is started to be guided to generate a vertical force F3 at the wings 4 to generate a head raising moment around a center of gravity, thereby altering the attack angle of the body. Thus, a vertical force F1 is generated at rear wings, and a vertical force F2 is generated at the main wings. At the time of guided flying, the wings 13 are longitudinally slid at necessary amount to alter the amount of moment generated around a center of gravity X by the force F2 to be applied to the main wings, thereby flying while varying the balanced attack angle of the missile.