Efficient vertical takeoff and landing aircraft

A technology for vertical take-off and landing of unmanned aerial vehicles, which is applied in the direction of aircraft, aircraft control, aircraft parts, etc., can solve the problems of local structural stress concentration and reduce the bearing efficiency of the wing structure, so as to reduce the structural weight, improve the structural bearing efficiency and Overall rigidity and strength, the effect of improving safety and reliability

Pending Publication Date: 2017-05-17
北京天宇新超航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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 circula

Method used

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  • Efficient vertical takeoff and landing aircraft
  • Efficient vertical takeoff and landing aircraft
  • Efficient vertical takeoff and landing aircraft

Examples

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Example Embodiment

[0040] Example 1

[0041] Figure 1~3 Shown are the basic structural layout and operation mode of a new type of vertical take-off and landing aircraft of the present invention. The aircraft includes a fuselage 1, the upper wing of the fuselage 1, the propeller power unit 3 on both sides of the wing 2, and the aileron control rudder surface 10, the vertical tail 4 and the vertical tail control rudder surface 11 on the rear side of the upper fuselage , The tiltable and fully movable horizontal tail 5 at the tail of the fuselage 1 and the propeller power unit 6 mounted on the horizontal tail. The fuselage 1 further includes a tilting actuation mechanism 7 for controlling the deflection of the wing and a device that can be used for coasting and landing. Front landing gear 8 and rear landing gear 9.

[0042] The propeller power unit 3 and the wing 2 are relatively fixed, and they are deflected together by the tilting actuator 7 during the flight mode conversion process. The wing power ...

Example Embodiment

[0048] Example 3

[0049] Based on the technical solution of the present invention, the inventor has carried out a lot of creative work from the initial design of the aircraft to the later verification test flight. During the test flight, the inventor found that for the vertical take-off and landing fixed-wing aircraft, the use of different propellers will affect the The flight efficiency under different flight conditions has a significant impact. In order to further clarify this difference, the inventor used the aircraft of the technical solution of the present invention to conduct test flights in the two states of vertical take-off and landing and fixed-wing cruise with different propellers under the same flight conditions, and tested the aircraft under the same flight conditions. The minimum throttle required for the power unit in a stable state was recorded, and the recorded results are shown in the following table:

[0050]

[0051] It can be seen from the above table that al...

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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...

Claims

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Application Information

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IPC IPC(8): B64C27/26B64C27/28B64C27/08B64C27/52B64C9/00B64C25/34B64C3/38
CPCB64C3/38B64C9/00B64C25/34B64C27/08B64C27/26B64C27/28B64C27/52B64C2009/005
Inventor 胡龙王一博
Owner 北京天宇新超航空科技有限公司
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