CN219115754U

CN219115754U - Solar energy continuation of journey double wing unmanned aerial vehicle

Info

Publication number: CN219115754U
Application number: CN202223591222.4U
Authority: CN
Inventors: 卢立学; 徐宁; 刘思璇; 吴世源
Original assignee: Yangtze River Delta Solar Photovoltaic Technology Innovation Center
Current assignee: Yangtze River Delta Solar Photovoltaic Technology Innovation Center
Priority date: 2022-12-30
Filing date: 2022-12-30
Publication date: 2023-06-02
Anticipated expiration: 2032-12-30

Abstract

The embodiment of the application provides a solar energy continuation of journey double wing unmanned aerial vehicle. The unmanned aerial vehicle includes the unmanned aerial vehicle main part, connect in the first wing of the both sides of unmanned aerial vehicle main part, connect in the mounting bracket of one side of first wing, connect the mounting bracket is kept away from the second wing of the one end of first wing, set up polylith first photovoltaic cell board on the first wing, set up polylith second photovoltaic cell board on the second wing, first photovoltaic cell board with the second photovoltaic cell board is used for converting sunlight into the confession unmanned aerial vehicle flight's electric energy, adjacent two first photovoltaic cell board is the connection of predetermineeing the angle and makes adjacent two first photovoltaic cell board enclose into first radiating space and/or adjacent two second photovoltaic cell board is the connection of predetermining the angle and makes adjacent two second photovoltaic cell board enclose into the second radiating space. The unmanned aerial vehicle has strong endurance and good heat dissipation effect, and can prolong the service life.

Description

Solar energy continuation of journey double wing unmanned aerial vehicle

Technical Field

The application relates to the technical field of solar photovoltaic brackets, in particular to a solar energy continuous double-wing unmanned plane.

Background

Unmanned aerial vehicles, abbreviated as "unmanned aerial vehicles", abbreviated as "UAVs", are unmanned aerial vehicles that are operated by means of radio remote control devices and self-contained programmed control devices, or are operated autonomously, either entirely or intermittently, by an onboard computer. Unmanned aircraft tend to be more suitable for tasks that are too "fooled, messy, or dangerous" than manned aircraft. Unmanned aerial vehicles can be classified into military and civilian applications according to the field of application.

Most of the existing unmanned aerial vehicle is affected by a power source, the endurance time is short, the unmanned aerial vehicle cannot continuously fly on the sky for cruising for a long time, and the fuel is adopted as the power source to consume more energy, so that environmental pollution is caused, and energy conservation and environmental protection are not facilitated.

In the related art, the unmanned plane adopts solar energy as a power source, is clean and pollution-free, is beneficial to energy conservation and environmental protection, can absorb solar energy for a long time to charge a high-energy battery when flying at high altitude, and greatly prolongs the endurance time, however, in order to ensure the endurance capacity, the wings of the existing solar unmanned plane are longer, the total length of the wings on two sides can reach hundreds of meters, so that the plane is huge and difficult to manufacture, and in addition, the heat dissipation of a photovoltaic panel is an important problem affecting the service life.

Disclosure of Invention

In view of this, it is necessary to provide a double-wing unmanned aerial vehicle with strong endurance, good heat dissipation effect and long service life.

The embodiment of the application provides a solar energy continuous double-wing unmanned plane, which comprises an unmanned plane main body; the first wings are connected to two sides of the unmanned aerial vehicle main body; the mounting frame is connected to one side of the first wing; the second wing is connected with one end of the mounting frame far away from the first wing; the first wing is provided with a plurality of first photovoltaic cell panels, the second wing is provided with a plurality of second photovoltaic cell panels, the first photovoltaic cell panels and the second photovoltaic cell panels are used for converting sunlight into electric energy for flying of the unmanned aerial vehicle, and two adjacent photovoltaic cell panels are bent and connected at a preset angle so that two adjacent photovoltaic cell panels enclose a first heat dissipation space and/or two adjacent photovoltaic cell panels are bent and connected at a preset angle so that two adjacent photovoltaic cell panels enclose a second heat dissipation space.

In one embodiment, the first wing is a lower wing and the second wing is an upper wing.

In one embodiment, a plurality of the first photovoltaic panels are disposed on a surface of the first wing proximate the mounting frame.

In one embodiment, a plurality of the second photovoltaic panels are disposed on a surface of the second wing remote from the mounting frame.

In one embodiment, a plurality of the first photovoltaic cell panels are sequentially connected along a first direction and located on the same plane.

In one embodiment, two adjacent second photovoltaic cell panels are bent and connected at a preset angle, so that the two adjacent second photovoltaic cell panels enclose to form the second heat dissipation space.

In one embodiment, the connecting line between the two adjacent bending connected second photovoltaic panels extends along a second direction, and the second direction is perpendicular to the first direction.

In one embodiment, the plurality of first photovoltaic cell panels on the first wing are located on the same plane and are arranged in a matrix, and the first photovoltaic cell panels comprise a plurality of rows of first photovoltaic cell panels along the second direction, and the plurality of first photovoltaic cell panels of each row of first photovoltaic cell panels are sequentially connected along the first direction.

In one embodiment, the plurality of second photovoltaic panels on the second wing are divided into a plurality of rows of second photovoltaic panels along the second direction, and in each row of second photovoltaic panels, two adjacent second photovoltaic panels enclose to form the second heat dissipation space.

In one embodiment, two adjacent second photovoltaic panels are located on the same plane along the second direction.

Compared with the related art, in the solar energy continuous double-wing unmanned plane provided by the embodiment of the application, a plurality of first photovoltaic cell panels are arranged on the first wing, a plurality of second photovoltaic cell panels are arranged on the second wing, and the first photovoltaic cell panels and the second photovoltaic cell panels are used for converting sunlight into electric energy for the unmanned plane to fly; in addition, two adjacent first photovoltaic cell boards are in preset angle bending connection, so that two adjacent first photovoltaic cell boards enclose to form a first heat dissipation space and/or two adjacent second photovoltaic cell boards are in preset angle bending connection, so that two adjacent second photovoltaic cell boards enclose to form a second heat dissipation space, the heat dissipation of the photovoltaic cell boards is facilitated, and accordingly reliability and service life of the photovoltaic cell boards can be improved.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the related art, the drawings that are required to be used in the embodiments or the related technical descriptions will be briefly described below, and it is apparent that the drawings in the following description are only embodiments of the present application, and other drawings may be obtained according to the provided drawings without inventive effort to those of ordinary skill in the art.

Fig. 1 is a perspective view of a solar energy continuous double-wing unmanned plane provided in an embodiment of the present application.

Detailed Description

In order to facilitate an understanding of the present application, a more complete description of the present application will now be provided with reference to the relevant figures. Preferred embodiments of the present application are shown in the accompanying drawings. This application may, however, be embodied in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

It will be understood that when an element is referred to as being "fixed to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "inner", "outer", "left", "right" and the like are used herein for illustrative purposes only and do not represent the only embodiment.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and/or" as used herein includes any and all combinations of one or more of the associated listed items.

Referring to fig. 1, the embodiment of the present application provides a solar energy endurance double-wing unmanned aerial vehicle 10, where the solar energy endurance double-wing unmanned aerial vehicle 10 includes an unmanned aerial vehicle main body 11; a first wing 12 connected to both sides of the unmanned aerial vehicle body 11; a mounting bracket 13 attached to one side of the first wing 12; a second wing 14 connected to an end of the mounting frame 13 remote from the first wing 12; the first wing 12 is provided with a plurality of first photovoltaic cell panels 15, the second wing 14 is provided with a plurality of second photovoltaic cell panels 16, the first photovoltaic cell panels 15 and the second photovoltaic cell panels 16 are used for converting sunlight into electric energy for the unmanned aerial vehicle 10 to fly, two adjacent first photovoltaic cell panels 15 are bent and connected at a preset angle so that two adjacent first photovoltaic cell panels 15 enclose to form a first heat dissipation space and/or two adjacent second photovoltaic cell panels 16 are bent and connected at a preset angle so that two adjacent second photovoltaic cell panels 16 enclose to form a second heat dissipation space 161. In this embodiment, two adjacent second photovoltaic panels 16 are bent and connected at a preset angle, so that the two adjacent second photovoltaic panels 16 enclose a second heat dissipation space 161 for schematic illustration.

The first wing 12 is a lower wing and the second wing 14 is an upper wing.

The first photovoltaic cell panel 15 and the second photovoltaic cell panel 16 may be lightweight photovoltaic cells, which is beneficial to reduce the overall weight of the unmanned aerial vehicle 10.

The mounting frame 13 can adopt aviation aluminum 6063, so that the connection and supporting strength are guaranteed, and the effect of light weight can be achieved.

The first photovoltaic cell panels 15 may be sequentially connected in series, and the second photovoltaic cell panels 16 may also be sequentially connected in series, which is specifically set and selected according to actual needs, which is not specifically limited in this application.

In this embodiment, a plurality of first photovoltaic panels 15 are disposed on a surface of the first wing 12 near the mounting frame 13. A plurality of the second photovoltaic panels 16 are disposed on a surface of the second wing 14 remote from the mounting frame 13. Specifically, a plurality of the first photovoltaic panels 15 may be sequentially connected along the first direction D1 and located on the same plane. The two adjacent second photovoltaic panels 16 are bent and connected at a preset angle, so that the two adjacent second photovoltaic panels 16 enclose the second heat dissipation space 161.

Further, the connecting line between the two adjacent bending-connected second photovoltaic panels 16 extends along a second direction, and the second direction is perpendicular to the first direction D1. The plurality of first photovoltaic cell panels 15 on the first wing 12 are located on the same plane and are arranged in a matrix, and the first photovoltaic cell panels 15 comprise a plurality of rows of first photovoltaic cell panels 15 along the second direction D2, and each row of first photovoltaic cell panels 15 is sequentially connected with the plurality of first photovoltaic cell panels 15 along the first direction D1. The plurality of second photovoltaic panels 16 on the second wing 14 are divided into a plurality of rows of second photovoltaic panels 16 along the second direction D2, and in each row of second photovoltaic panels 16, two adjacent second photovoltaic panels 16 enclose to form the second heat dissipation space 161. Along the second direction D2, two adjacent second photovoltaic panels 16 are located on the same plane.

Compared with the related art, in the solar energy continuous double-wing unmanned aerial vehicle 10 provided by the embodiment of the application, the first wing 12 is provided with the plurality of first photovoltaic cell panels 15, the second wing 14 is provided with the plurality of second photovoltaic cell panels 16, and the first photovoltaic cell panels 15 and the second photovoltaic cell panels 16 are used for converting sunlight into electric energy for the unmanned aerial vehicle to fly; in addition, two adjacent first photovoltaic cell panels 15 are connected in a preset angle bending mode so that two adjacent first photovoltaic cell panels 15 enclose to form a first heat dissipation space and/or two adjacent second photovoltaic cell panels 16 are connected in a preset angle bending mode so that two adjacent second photovoltaic cell panels 16 enclose to form a second heat dissipation space 161, and the design is favorable for heat dissipation of the photovoltaic cell panels, so that reliability and service life of the photovoltaic cell panels can be improved.

The foregoing examples merely represent embodiments of the present application, which are described in more detail and are not to be construed as limiting the scope of the utility model. It should be noted that it would be apparent to those skilled in the art that various modifications and improvements could be made without departing from the spirit of the present application, which would be within the scope of the present application. Accordingly, the scope of protection of the present application is to be determined by the claims appended hereto.

Claims

1. The utility model provides a solar energy twin-wing unmanned aerial vehicle that continues to journey, its characterized in that, solar energy twin-wing unmanned aerial vehicle that continues to journey includes:

an unmanned aerial vehicle main body;

the first wings are connected to two sides of the unmanned aerial vehicle main body;

the mounting frame is connected to one side of the first wing;

the second wing is connected with one end of the mounting frame far away from the first wing;

the first wing is provided with a plurality of first photovoltaic cell panels, the second wing is provided with a plurality of second photovoltaic cell panels, the first photovoltaic cell panels and the second photovoltaic cell panels are used for converting sunlight into electric energy for flying of the unmanned aerial vehicle, and two adjacent photovoltaic cell panels are bent and connected at a preset angle so that two adjacent photovoltaic cell panels enclose a first heat dissipation space and/or two adjacent photovoltaic cell panels are bent and connected at a preset angle so that two adjacent photovoltaic cell panels enclose a second heat dissipation space.

2. The solar cruising double wing unmanned aircraft according to claim 1, wherein the first wing is a lower wing and the second wing is an upper wing.

3. The solar cruising double wing unmanned aerial vehicle of claim 1, wherein a plurality of the first photovoltaic panels are disposed on a surface of the first wing proximate the mounting bracket.

4. The solar cruising double wing unmanned aerial vehicle of claim 1, wherein a plurality of the second photovoltaic panels are disposed on a surface of the second wing remote from the mounting frame.

5. The solar cruising double wing unmanned aerial vehicle of claim 1, wherein a plurality of the first photovoltaic panels are connected in sequence along a first direction and are located on the same plane.

6. The solar cruising double-wing unmanned aerial vehicle of claim 5, wherein two adjacent second photovoltaic panels are bent and connected at a preset angle, so that the two adjacent second photovoltaic panels enclose the second heat dissipation space.

7. The solar cruising double wing unmanned aerial vehicle of claim 6, wherein a connecting line between the second photovoltaic panels of two adjacent bending connection runs along a second direction, the second direction being perpendicular to the first direction.

8. The solar cruising double-wing unmanned aerial vehicle of claim 7, wherein the plurality of first photovoltaic panels on the first wing are located on the same plane and are arranged in a matrix, and the solar cruising double-wing unmanned aerial vehicle comprises a plurality of rows of first photovoltaic panels along the second direction, and the plurality of first photovoltaic panels of each row of first photovoltaic panels are sequentially connected along the first direction.

9. The solar cruising double-wing unmanned aerial vehicle according to claim 7, wherein a plurality of the second photovoltaic panels on the second wing are divided into a plurality of rows of the second photovoltaic panels along the second direction, and two adjacent second photovoltaic panels in each row of the second photovoltaic panels form the second heat dissipation space.

10. The solar cruising double wing unmanned aerial vehicle of claim 9, wherein two adjacent second photovoltaic panels are located on the same plane along the second direction.