Folding-wing unmanned aerial vehicle and launching method thereof

A technology of unmanned aerial vehicles and folding wings, which is applied in the direction of launch/drag transmission, fuselage, aircraft parts, etc., can solve the problems of fuselage rotation, small effective loading space, affecting the success rate of unmanned aerial vehicles, etc. The effect of launching success rate and improving stability

Pending Publication Date: 2019-07-09
浙江驰宇空天技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Traditional folding-wing UAVs generally use X-shaped airfoils, and the effective loading space of X-wing UAVs is small. Therefore, people have developed a Z-shaped folding UAV, see application number 201811601135.8 Published invention patent application, although the application overcomes the shortcomings of the traditional folding-wing UAV's small effective loading space, there are still technical defects:

Method used

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  • Folding-wing unmanned aerial vehicle and launching method thereof
  • Folding-wing unmanned aerial vehicle and launching method thereof
  • Folding-wing unmanned aerial vehicle and launching method thereof

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Embodiment 1

[0045] Example 1, see figure 1 , the application provides a folding wing UAV, including a fuselage 01, a front straight wing, a rear straight wing, a foldable vertical tail installed at the rear of the fuselage, and a foldable propeller assembly installed at the rear of the fuselage , one of the front straight wing and the rear straight wing is installed on the top surface of the fuselage, and the other is installed on the bottom surface of the fuselage, and both can be folded centered on the fuselage, Specifically, the front straight wing is installed on the top surface of the fuselage, including a left front straight wing 03 on the left side of the fuselage and a right front straight wing 02 on the right side of the fuselage. The straight wing and the left front straight wing can be folded back centered on the fuselage; the rear straight wing is installed on the bottom surface of the fuselage, including the left rear straight wing 06 and the The right rear straight wing 04 ...

Embodiment 2

[0061] Embodiment 2, the present invention also provides a launching method of the above-mentioned folding-wing unmanned aerial vehicle, comprising the following steps:

[0062] Step 1, the folding wing UAV is in a fully folded state and placed in the corresponding launch tube A;

[0063] Among them, the fully folded state of the folding wing UAV refers to:

[0064] For the front straight wing, the left front straight wing and the right front straight wing are folded back to coincide with the fuselage, and are located at the cut flat position on the top of the fuselage;

[0065] For the rear straight wing, the left rear straight wing and the right rear straight wing are folded forward to coincide with the fuselage and are located at the cut flat position at the bottom of the fuselage;

[0066] For the vertical fins, the left vertical fin and the right vertical fin are folded down to coincide with the said fuselage, the left vertical fin is located on the left side of the fuse...

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Abstract

The invention relates to a folding-wing unmanned aerial vehicle. The folding-wing unmanned aerial vehicle comprises a vehicle body, a front straight wing, a rear straight wing, a folding vertical finwhich is installed on the afterbody of the vehicle body, and a folding propeller assembly at the rear end of the vehicle body. One of the front straight wing and the rear straight wing is installed onthe top face of the vehicle body, the other one is installed on the bottom face of the vehicle body, and the front straight wing and the rear straight wing can be folded with the vehicle body as thecenter. According to the folding-wing unmanned aerial vehicle, in the unfolding process, the front straight wing and the rear straight wing can be symmetrically unfolded on the left and right sides with the vehicle body as the center, so that in the unfolding process, no difference exists between the balance forces of the front straight wing and the rear straight wing to the unmanned aerial vehicle body on the two sides, rotation of the vehicle body is not easily caused, the stability of the unmanned aerial vehicle is improved, and then the launching success rate of the unmanned aerial vehicleis improved.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a folding-wing unmanned aerial vehicle and a launching method thereof. Background technique [0002] With the development of science and technology, folding-wing UAVs have developed rapidly due to their advantages of being able to quickly fold and effectively reduce the large space they occupy during transportation, launch, and delivery. [0003] Traditional folding-wing UAVs generally use X-shaped airfoils, and the effective loading space of X-wing UAVs is small. Therefore, people have developed a Z-shaped folding UAV, see application number 201811601135.8 Published invention patent application, although the application overcomes the shortcomings of the traditional folding-wing UAV's small effective loading space, there are still technical defects: [0004] During the unfolding process, the left and right sides of the Z-shaped folding wings are unfo...

Claims

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Application Information

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IPC IPC(8): B64C1/30B64F1/06
CPCB64C1/30B64F1/06
Inventor 陈松王成军薛艳峰田牧青孙鹏飞李铁关宗瑞郝晓夜曾林凯张洪立
Owner 浙江驰宇空天技术有限公司
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