The invention relates to a
composite wing aircraft with a
dihedral angle, which belongs to the technical field of aircrafts. The
composite wing aircraft with the
dihedral angle comprises an aircraft body, a left
composite wing, a right composite wing, a
tail wing and a
landing gear. An operation
system and airbore equipment are mounted in the aircraft body. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left side and the right side of the aircraft body. The
tail wing comprises a horizontal
tail wing and a vertical tail wing. The
landing gear uses a wheel type structure or a skid and wheel combined structure. A dihedral wing exerts an effect of stabilizingthe aircraft. The left composite wing comprises a wing axle, a front wing sheet, a rear outer wing sheet, a rear inner wing sheet, a dihedral wing sheet, a rotor wing and an engine. The rear outer wing sheet and the rear inner wing sheet both can rotate and swing around the wing axle. The rotating plane of the rotor wing is in a horizontal position. During the rotation of the rotor wing, flow fields of the upper and lower surfaces of the wing sheets can be improved to increase downwash
airflow and
delay airflow separations on the upper surfaces of the wing sheets. The composite wing aircraft with the
dihedral angle, provided by the invention, has the advantages of safety, high efficiency and high mobility.