The invention belongs to the technical field of aviation, and particularly relates to an aircraft. The aircraft comprises a fuselage, and a main wing arranged on the fuselage. Connecting rods are arranged on the two sides of the fuselage, fixedly connected with the main wing, and arranged in the length direction of the fuselage. Vertical tails are arranged at the rear ends of the two connecting rods correspondingly. A horizontal tail is connected between the two vertical tails. Vertical rotors are arranged on the two connecting rods correspondingly. Canards and undercarriages rotating coaxially with the canards are rotationally connected between the front ends of the two connecting rods and the fuselage correspondingly. Tilting rotors are mounted on the undercarriages correspondingly. Thecanards, the main wing and the horizontal tails of three wing surfaces form a frame structure, the rigidity of the overall structure and a light weight can be guaranteed, the spanwise size is reduced,and influences of crosswind on the whole aircraft are reduced; the main wing is higher than the canards, and strong interference of downwash airflow of the canards can be avoided; and the vertical tails serve as the rear undercarriages, the weight is lowered, the flight aerodynamic resistance is reduced, and the problems that an existing aircraft is complex in structure and poor in flight aerodynamic efficiency are solved.