The invention relates to a double-variable-pitch-propeller aircraft, belonging to the technical field of aviation. The double-variable-pitch-propeller aircraft comprises a fuselage, a tail device, a left wing, a right wing, a left variable-pitch rotor wing, a right variable-pitch rotor wing and an undercarriage. An operation and control system, airborne equipment and energy equipment are equipped in the fuselage. The tail device comprises a left tail propeller, a right tail propeller and a vertical tail. The left variable-pitch rotor wing and the right variable-pitch rotor wing are the same in structure, parameter and working principle and are symmetrically arranged at the left and right sides of the fuselage, so as to supply lift and thrust to the aircraft. The right variable-pitch rotor wing comprises an engine, a main shaft, an electric brush device, a wheel hub and two or four identical propellers which are uniformly distributed around the wheel hub. A main shaft of the right variable-pitch rotor wing is in counterclockwise rotation, at the right side of the main shaft, propeller vanes forwards move at low incidence to generate an upward towing force, and at the left side of the main shaft, the propeller vanes backwards flap at high incidence to generate a forward thrust force, so that the aircraft moves forwards. The aircraft is applied to a variety of tasks, such as aerial photography, geographical mapping, agriculture-forestry-husbandry operation, military reconnaissance and emergency rescue and disaster relief.