PURPOSE: To take off and land even when a place is narrow, and improve autonomous stability and safety at forced landing time by arranging a central girder between a column of the fuselage and a vertical tail, arranging a main wing constituting member by plane moderate angle shaped side girder materials, arranging the vertical tail, a horizontal tail and a propeller having a prime mover, and controlling these by a radio transmitter.

CONSTITUTION: A central girder material 3b on the central upper side of the fuselage 2 is fixed to a column 3d and a vertical tail 4, and plane moderate angle-shaped side girder material 3c are fixed to the front end of the central girder material 3b and both tips of a beam material 3e, and a main wing sheet 3a of a flexible raw material is fixed to these. A horizontal tail 5 whose whole wing swings is arranged on the side of the vertical tail 4. A propeller rotated by a prime mover 6 is arranged in the vicinity of the center of gravity of an aircraft body 1, and the control mechanism is controlled by a radio transmitter 13 together with a control mechanism of the vertical tail 4 and the horizontal tail 5. Since the main wing sheet 3a has the large area and the horizontal tail 5 can swing the whole wing, a ground run can be shortened even at low speed, and autonomous posture restoring force is improved.