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Fairing structure of medium-sized unmanned aerial vehicle with high lift-drag ratio

A high lift-to-drag ratio, fairing technology, applied in the field of drones, can solve problems affecting the flight effect and equipment of drones

Inactive Publication Date: 2021-04-09
北京北航天宇长鹰无人机科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Similarly, drones will encounter various working environments during mission execution; under the influence of airflow, it will directly affect the flight effect and equipment of drones.

Method used

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  • Fairing structure of medium-sized unmanned aerial vehicle with high lift-drag ratio
  • Fairing structure of medium-sized unmanned aerial vehicle with high lift-drag ratio
  • Fairing structure of medium-sized unmanned aerial vehicle with high lift-drag ratio

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Effect test

Embodiment 1

[0041] This embodiment provides a fairing structure for a medium-sized unmanned aerial vehicle with a high lift-to-drag ratio. The fairing structure is arranged at the wing root of the wing 4, connects the wing root and the fuselage 5, and adopts a small-angle chamfer For rectification, the angle between the fuselage and the wing is greater than 90°; the shape of the wing-body junction of the UAV is as follows figure 1 Shown (schematic diagram of wing structure without fairing);

[0042] The fairing structure is as figure 2 Shown (rectification method 1), including:

[0043] Leading edge rectification structure 1, the leading edge rectifying structure is an arc structure; the leading edge sweep angle of the leading edge rectifying structure is 40°; the leading edge extension length is 370mm, the leading edge radius is 355mm, and the spanwise length is 300mm.

[0044] The spanwise rectification structure 2, the number of the spanwise rectification structure having profile t...

Embodiment 2

[0050] This embodiment provides a fairing structure for a medium-sized unmanned aerial vehicle with a high lift-to-drag ratio. The difference from Embodiment 1 is that it does not include a "span-wise rectifying structure"; image 3 As shown, including front rectification structure 1 and middle and rear rectification structure 3; (rectification mode 2)

[0051] Specifically, similar to wing strakes, the maximum thickness of the fairing does not exceed the maximum thickness of the largest airfoil at the wing root, and is only added before the maximum thickness of the wing, with a sharper leading edge shape, the purpose of which is The transition between the leading edge of the wing and the fuselage is smooth, and the boundary layer at the stagnation point of the leading edge is eliminated as much as possible to prevent the flow separation of the boundary layer caused by the sharp change of speed. Fairing form such as image 3 shown. The length of the front rectification area ...

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Abstract

The invention relates to a fairing structure of a medium-sized unmanned aerial vehicle with a high lift-drag ratio. The fairing structure is arranged at the wing root of the wing, is connected with the wing root of the wing and the fuselage, and adopts small-angle chamfer rectification; the included angle between the fuselage and the wings is larger than 90 degrees. The fairing structure provided by the invention is positioned at the joint of the wing and the fuselage, and the streamline shape of the fairing structure seals the joint of the wing and the fuselage, so that the fairing structure has dual functions of butting the wing body and reducing air resistance. Several different fairing forms are designed through curved surface creation, aerodynamic analysis and wind tunnel verification are carried out through numerical simulation calculation, and then the fairing shape with good manufacturability and rectification effect is selected.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a fairing structure of an unmanned aerial vehicle. Background technique [0002] In the existing flight equipment, fairings are added to aircraft, rockets, satellites, etc., to reduce the resistance exposed to the flight equipment and adjust the influence of airflow. During the flight of flight equipment, a large airflow will be generated, which will easily cause certain damage to the engine and internal components. The increase of the fairing can effectively alleviate the above damage. [0003] Similarly, drones will encounter various working environments during mission execution; under the influence of airflow, it will directly affect the flight effect and equipment of drones. Contents of the invention [0004] The purpose of the present invention is to provide a fairing for a medium-sized unmanned aerial vehicle with a high lift-to-drag ratio by designing and improv...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C7/00B64C3/58B64C1/26B64C39/02
CPCB64C1/26B64C3/58B64C7/00B64C39/02
Inventor 梁阳王晨先王靖欢
Owner 北京北航天宇长鹰无人机科技有限公司
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