Efficient vertical takeoff and landing aircraft

Abstract

The invention relates to an efficient vertical takeoff and landing aircraft, and discloses an efficient vertical takeoff and landing fixed-wing unmanned aerial vehicle, which comprises a fuselage, a wing, a horizontal tail, a vertical tail, a control surface, a power unit, a tilting mechanism and an undercarriage. The tilting mechanism controls the tilting angle of the wing and the horizontal tail to realize the mutual conversion of a vertical takeoff and landing state and a flat flight state of the aircraft. A propeller power unit is arranged on each of the wing and the horizontal tail, a part of lift at the vertical takeoff and landing stage is provided by the wing propeller power unit, and the tail propeller power unit is responsible for the aircraft pitch balance adjustment; the power device installed on the wing is closed in the flat flight state, and the tail propeller power unit provides forward thrust in order to improve the efficiency of the aircraft in a cruising state. Compared with the existing vertical takeoff and landing fixed-wing unmanned aerial vehicle design scheme, the flight aerodynamic efficiency of the aircraft in the fixed-wing flat flight state is taken into account while the layout is simplified, and reliability and practicability are relatively high.

Description

technical field [0001] The invention belongs to the field of aviation vehicle design, and in particular relates to an efficient and multi-purpose vertical take-off and landing unmanned aerial vehicle capable of achieving fixed-wing cruising flight efficiency. Background technique [0002] At present, the most common unmanned aerial vehicles are mainly in the form of multi-rotor and fixed-wing. The structure of multi-rotor aircraft is simple, relying solely on the rotor to provide lift, and the control response is relatively sensitive. Due to the lack of propulsion power and low aerodynamic efficiency, its forward flight speed is slow, its wind resistance is weak, and its endurance is poor; the fixed-wing UAV adopts a flight layout that has been extensively verified, with high aerodynamic efficiency and can achieve long flight time. Time cruising flight and high flight speed, but this type of aircraft must reach a certain speed during take-off and landing, and has certain req...

AI Technical Summary

Problems solved by technology

In the prior art represented by the above-mentioned patents, the wings all adopt the main beam structure. The root of the wing is connected to the fuselage through a circular tube, and the load of the wing is transmitted to the fuselage through this circular tube. Due to the shape limitation, the connection The cross-sectional area of ​​the circular tube is much smaller than the cross-sectional area of ​​the wing root, which is equivalent to a sudden change in the cross-section of the wing structure at the connection point, resulting in a significant stress concentration phenomenon in the local structure, which greatly reduces the weight of the wing. load-carrying efficiency of the structure

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