The invention relates to a blind window wing type tilt rotor aircraft and belongs to air vehicles. A front small tilt rotation wing and a rear small tilt rotation wing are arranged on the front part and the rear part of an aircraft body respectively; an engine I, an engine II, an engine III and an engine IV are respectively connected with the front small tilt rotation wing and the rear small tilt rotation wing; a propeller I, a propeller II, a propeller III and a propeller IV are respectively connected with the engine I, the engine II, the engine III and the engine IV; hydraulic supporting rods are arranged in the middles of the front small tilt rotation wing and the rear small tilt rotation wing; a blind window wing is arranged at the gravity center of the middle of the aircraft body; a vertical stabilization surface and a horizontal stabilization surface are formed on the tail part of the aircraft body; a rudder is arranged on the vertical stabilization surface and an elevating rudder is arranged on the horizontal stabilization surface. The blind window wing type tilt rotor aircraft has the advantages that the structure is novel, the short-distance taking off and landing and the vertical lifting are achieved, the forward speed is high, the control is easy, the safety is high, and the occurrence of accidents can be effectively reduced.
Blind window wing type tilt rotor aircraft
2016-01-06
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Methodology for Estimating Wing Weights for Conceptual Tilt-Rotor and Tilt-Wing Aircraft
British Library Conference Proceedings | 1992
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