| 摘要 |
PROBLEM TO BE SOLVED: To solve such a problem that attitude control of a missile is difficult because the missile rotates when the steering method is a rolling airframe method.SOLUTION: A missile 10 includes: an air frame 11 having an axis in the roller axis direction; an outlying body 12 which rotates around the roller axis on the outer circumferential surface of the air frame 11; a steering part 21 which has steering blades 15, 16 disposed in the radial outer direction of the axis on the outlying body 12 and steers the steering blades 15, 16; a rotation support mechanism 22 which supports the steering part 21 and the outlying body 12 around the roller axis by means of aerodynamic steering force generated by flight of the air frame 11; a detection part 23 which detects rotating position information of the rotation support mechanism 22; and a steering driving part 24 which performs steering drive of the steering blades 15, 16 based on the rotation position information from the detection part 23. |
