Overall aerodynamic layout and short-distance taking-off and landing method of double-engine unmanned aerial vehicle

An aerodynamic layout and unmanned aerial vehicle technology, applied in the aviation field, can solve the problems of low thrust weight, impact of braking efficiency, long take-off and roll distance, etc., and achieve the effect of short take-off and landing distance, high lift-to-drag ratio, and wide flight speed range.

Inactive Publication Date: 2018-08-10
CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] 1. Usually a single propeller engine with low thrust weight and long take-off and run distance
[0004] 2. Affected by the braking performance, the landing and rolling distance is long

Method used

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  • Overall aerodynamic layout and short-distance taking-off and landing method of double-engine unmanned aerial vehicle
  • Overall aerodynamic layout and short-distance taking-off and landing method of double-engine unmanned aerial vehicle
  • Overall aerodynamic layout and short-distance taking-off and landing method of double-engine unmanned aerial vehicle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0030] a. If figure 1 As shown, the UAV is composed of a fuselage, a large-scale radome, wings, a nacelle, a propeller, and a V tail.

[0031] b. If figure 2 As shown, the fuselage adopts a ship-shaped section.

[0032] c. If image 3 As shown, the rear section of the fuselage is equipped with arresting hooks.

[0033] d. If Figure 4 As shown, the wing aspect ratio is 15-20. The plane shape of the wing is a combination of rectangle and trapezoid.

[0034] e. The wing adopts a high lift-to-drag ratio supercritical airfoil, laminar flow airfoil or supercritical laminar flow airfoil.

[0035] f. If Figure 4 As shown, flaps, flaperons, and ailerons are arranged at the rear end of the wing.

[0036] g. If figure 1 As shown, the two engines and propellers are arranged through the wing nacelles.

[0037] h. If figure 1 As shown, the shape of the fuselage and the wing are blended and transitioned.

[0038] i. Use liftable wheel chocks to block UAVs. When the UAV engine ...

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Abstract

The invention relates to an overall aerodynamic layout of a double-engine unmanned aerial vehicle. The overall aerodynamic layout of the double-engine unmanned aerial vehicle is characterized in thatthe unmanned aerial vehicle comprises a vehicle body (1), a large-size radome (2), a wing (4), short cabins (3), propellers (5), a V tail (6) and a blocking hood (11); the section of the vehicle body(1) is in a ship shape, the span-chord ratio of the wing (4) is 15:25, and the vehicle body (1) and the wing (4) are in fused transition in shape; a flap (7), a flaperon (8) and an aileron (9) are arranged on the wing (4), and a lifting rudder (10) is arranged on the V tail (6); and engines are mounted on the inner section of the front edge of the wing through the short cabins (3), and the propellers (5) are mounted at the front ends of the short cabins. The unmanned aerial vehicle adopting the short-distance taking-off and landing layout can meet the overall, aerodynamic, structural and taking-off-and-landing-performance requirements and has the advantages of being wide in flying speed range, high in lift-to-drag ratio, short in taking-off and landing distance and the like, and the short-distance taking off and landing unmanned aerial vehicle layout can be used for aerodynamic layout design of scouting and attaching integrated unmanned aerial vehicles, attaching-type unmanned aerial vehicles, scouting-type unmanned aerial vehicles and special unmanned aerial vehicles.

Description

technical field [0001] The invention belongs to the field of aviation, and relates to an overall aerodynamic layout adopted in the aerodynamic layout of a high lift-to-drag ratio twin-engine unmanned aerial vehicle and a take-off and landing usage method. Background technique [0002] The integrated surveillance drone generally adopts a conventional layout, and there are the following problems: [0003] 1. It is usually a single propeller engine with relatively low thrust and long take-off and run distance. [0004] 2. Affected by the braking performance, the landing and rolling distance is long. [0005] 3. In order to carry more fuel, install more equipment, and improve combat effectiveness, the internal space is tight. Contents of the invention [0006] The purpose of the invention is to propose a general aerodynamic layout of a dual-engine unmanned aerial vehicle capable of short take-off and landing. [0007] Technical solution of the present invention is: [0008...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/02
CPCB64C39/02B64U70/60B64U30/10B64U10/25B64U50/13
Inventor 薛睿程熙魏松原刘英杰刘远平李屹东
Owner CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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