WO2020024423A1

WO2020024423A1 - Aircraft, solar cell system, wing, and manufacturing method therefor

Info

Publication number: WO2020024423A1
Application number: PCT/CN2018/108838
Authority: WO
Inventors: 吴桂弟
Original assignee: 东汉太阳能无人机技术有限公司
Priority date: 2018-08-02
Filing date: 2018-09-29
Publication date: 2020-02-06
Also published as: CN109103284A

Abstract

An aircraft, a solar cell system (100), a wing (200), and a manufacturing method for the wing (200). the solar cell system (100) comprises a first encapsulation layer (2), a second encapsulation layer (3), and one or a plurality of photovoltaic cell modules (1); the second encapsulation layer (3) is arranged exactly opposite to the first encapsulation layer (2); the photovoltaic cell modules (1) are sandwiched between the first encapsulation layer (2) and the second encapsulation layer (3), each photovoltaic cell module (1) being electrically connected, and each photovoltaic cell module (1) comprising a plurality of electrically connected photovoltaic cell chips (11). The present solar cell system (100) modularises the photovoltaic cell chips (11) for convenient incorporation with a wing segment of the wing (200), improving mounting efficiency.

Description

Aircraft, solar battery system, wing and manufacturing method thereof

Cross-reference to related applications

This application claims the priority of Chinese Patent Application No. CN201810873114.5 filed in China on August 02, 2018, the entire contents of which are incorporated herein by reference.

Technical field

The present disclosure relates to, but not limited to, the technical field of aircraft, and in particular, to an aircraft, a solar cell system, a wing, and a method of manufacturing the wing.

Background technique

With the development of photovoltaic technology, solar energy has been used more and more widely. Among them, aircraft using solar energy as a power source is a very common application field. Taking a fixed-wing aircraft as an example, its wings usually need to lay a large number of photovoltaic cell chips to form an array of photovoltaic cell chips, perform photoelectric conversion through each photovoltaic cell chip, and provide energy to the parts of the aircraft through special circuits and controllers. .

However, when laying photovoltaic cell chips on the wing, the photovoltaic cell chips need to be installed on the wing one by one, the workload is large, the operation is complicated, and the installation efficiency is low.

It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of the present disclosure, and therefore may include information that does not constitute the prior art known to those of ordinary skill in the art.

Summary of the invention

The purpose of the present disclosure is to provide an aircraft, a solar cell system, a wing, and a method of manufacturing the wing, thereby at least to some extent overcoming one or more problems caused by the limitations and defects of the related technology.

According to an aspect of the present disclosure, a solar cell system is provided, the solar cell system includes:

First encapsulation layer;

A second encapsulation layer disposed opposite to the first encapsulation layer;

One or more photovoltaic cell modules are sandwiched between the first encapsulation layer and the second encapsulation layer, and each of the photovoltaic cell modules is electrically connected, and each of the photovoltaic cell modules includes a plurality of electrical connections Photovoltaic cell chip.

In an exemplary embodiment of the present disclosure, the photovoltaic cell chip is a gallium arsenide photovoltaic cell.

In an exemplary embodiment of the present disclosure, each of the photovoltaic cell chips in the same photovoltaic cell module is sequentially overlapped, and two adjacent photovoltaic cell chips are connected by a conductive material.

In an exemplary embodiment of the present disclosure, at least one of the first encapsulation layer and the second encapsulation layer is a high-barrier composite water-blocking film.

In an exemplary embodiment of the present disclosure, each of the photovoltaic cell modules is connected in parallel, and each photovoltaic cell chip of the same photovoltaic cell module is connected in series.

According to an aspect of the present disclosure, there is provided a wing including at least one wing segment, each of which is mounted with at least one solar cell system according to any one of the above.

In an exemplary embodiment of the present disclosure, the wing segment includes:

Skin, the solar cell system is adhered to the surface of the skin by an adhesive.

The skin is provided with an accommodating groove, and the solar cell system is cooperatively disposed in the accommodating groove, and is snapped or bonded to the inner wall of the accommodating groove.

In an exemplary embodiment of the present disclosure, the number of the wing segments is multiple and includes:

First wing segment

A second wing segment detachably connected to one end of the first wing segment;

The third wing segment is detachably connected to the other end of the first wing segment, and is disposed symmetrically with the second wing segment with respect to the first wing segment.

According to an aspect of the present disclosure, there is provided a method of manufacturing an airfoil, including:

Providing a solar cell system and a skin, the solar cell system is the solar cell system according to any one of the above;

Bonding the solar cell system to a surface of the skin through an adhesive;

Placing the skin to which the solar cell system is adhered in a vacuum chamber;

The inside of the vacuum chamber is heated to cure the adhesive.

Providing a mold and a solar cell system, wherein the solar cell system is the solar cell system according to any one of the above;

Inserting a filler into the mold;

Forming a skin by a molding process using the mold;

Removing the filler to form an accommodation groove;

Bonding the solar cell system into the containing groove through an adhesive;

Placing the skin to which the solar cell system is adhered in a vacuum chamber;

The inside of the vacuum chamber is heated to cure the adhesive.

Inserting the solar cell system into the mold;

A skin is formed by a molding process using the mold, and the skin exposes the solar cell system.

According to an aspect of the present disclosure, there is provided an aircraft including a wing according to any one of the above.

The disclosed aircraft, solar cell system, wing and manufacturing method of the wing can significantly improve the assembly efficiency of the on-board photovoltaic cell chip, especially for the on-board photovoltaic energy supply system with complex structure, which can be manufactured in combination with the shape of the wing Solar cell system to improve installation efficiency. Specifically, since a plurality of parallel photovoltaic cell modules are sandwiched between the first encapsulation layer and the second encapsulation layer, the plurality of photovoltaic cell modules are integrated into a solar cell system. During the installation, the solar cell may be installed. The system as a whole is integrated with the wing to avoid installing photovoltaic cell chips one by one, thereby improving the installation efficiency. At the same time, each photovoltaic cell module includes multiple electrically connected photovoltaic cell chips, and each photovoltaic cell module is also electrically connected, so it can receive light for power generation at the same time; the photovoltaic cell chip uses a thin and flexible solar conversion chip, which is easy to fit and install , Does not affect the aerodynamic shape of the wing.

It should be understood that the above general description and the following detailed description are merely exemplary and explanatory, and should not limit the present disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

The drawings herein are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure, and together with the description serve to explain the principles of the present disclosure. Obviously, the drawings in the following description are just some embodiments of the present disclosure. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

FIG. 1 schematically illustrates a top view of a solar cell system in an embodiment of the present disclosure.

FIG. 2 schematically illustrates a cross-sectional view when a solar cell system is not pressed in an embodiment of the present disclosure.

FIG. 3 schematically illustrates a cross-sectional view of a solar cell system after pressing according to an embodiment of the present disclosure.

FIG. 4 schematically illustrates a top view of a photovoltaic cell module of a solar cell system in an embodiment of the present disclosure.

FIG. 5 schematically illustrates a side view of a photovoltaic cell module of a solar cell system in an embodiment of the present disclosure.

FIG. 6 schematically illustrates an assembly view of an airfoil in an embodiment of the present disclosure.

FIG. 7 schematically illustrates an exploded view of an airfoil in an embodiment of the present disclosure.

FIG. 8 schematically illustrates a laminated structure of a solar cell system and a wing skin in an embodiment of the present disclosure.

FIG. 9 schematically illustrates a schematic diagram of an aircraft in an embodiment of the present disclosure.

FIG. 10 schematically illustrates a flowchart of a method of manufacturing an airfoil in an embodiment of the present disclosure.

FIG. 11 schematically illustrates a flowchart of a method of manufacturing an airfoil in an embodiment of the present disclosure.

FIG. 12 schematically illustrates a flowchart of a method of manufacturing an airfoil in an embodiment of the present disclosure.

In the picture: 100, solar cell system; 1, photovoltaic cell module; 11, photovoltaic cell chip; 12, conductive material; 13, conductive connector; 2, first packaging layer; 3, second packaging layer; 101, first Solar cell system; 102, second solar cell system; 103, third solar cell system; 4, first adhesive layer; 5, second adhesive layer; 6, back sheet; 7, adhesive layer; 200, machine Wing; 201, first wing segment; 202, second wing segment; 203, third wing segment; 2001, skin; 300, fuselage.

detailed description

Example embodiments will now be described more fully with reference to the accompanying drawings. However, the example embodiments can be implemented in various forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that the present invention will be comprehensive and complete, and the concept of the example embodiments will be fully conveyed To those skilled in the art. The drawings are merely schematic illustrations of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.

Although relative terms such as "up" and "down" are used in this specification to describe the relative relationship between one component and another component of the icon, these terms are used in this specification for convenience only, for example, according to the figures in the drawings. Direction of the examples described. It can be understood that if the device of the icon is turned upside down and turned upside down, the component described above will become the component below. When a structure is "on" another structure, it may mean that a structure is integrally formed on another structure, or that a structure is "directly" arranged on another structure, or that a structure is "indirectly" arranged on another structure through another structure. On other structures.

The terms “a”, “an”, “the”, “the”, and “at least one” are used to indicate the presence of one or more elements / components / etc .; the terms “include” and “having” are used to mean open-ended Included means that there may be additional elements / components / etc. In addition to the listed elements / components / etc; the terms "first", "second" and "third" etc. only Used as a marker, not a limit on the number of its objects.

An embodiment of the present disclosure provides a solar cell system, which can be used for a wing, the wing can have at least one wing section, and the solar cell system can be installed on any wing section. As shown in FIGS. 1-3, a solar cell system 100 according to an embodiment of the present disclosure may include a photovoltaic cell module 1, a first encapsulation layer 2, and a second encapsulation layer 3, where:

The first encapsulation layer 2 and the second encapsulation layer 3 are disposed to face each other. The number of photovoltaic cell modules 1 is multiple. Each photovoltaic cell module 1 is sandwiched between the first encapsulation layer 2 and the second encapsulation layer 3, and each photovoltaic cell module 1 is electrically connected. Each photovoltaic cell module 1 includes a plurality of photovoltaic cells. Of an electrically connected photovoltaic cell chip 11.

The solar cell system 100 according to the embodiment of the present disclosure can significantly improve the assembly efficiency of the on-board photovoltaic cell chip 11. Especially for the on-board photovoltaic energy supply system with a complex structure, the solar cell system can be manufactured in combination with the shape of the wings to improve the installation efficiency. . Specifically, since a plurality of electrically connected photovoltaic cell modules 1 are sandwiched between the first encapsulating layer 2 and the second encapsulating layer 3, the plurality of photovoltaic cell modules 1 are integrated into one solar cell system 100. The solar cell system 100 can be combined with the wing segment of the wing as a whole to avoid installing the photovoltaic cell chips 11 one by one, thereby improving the installation efficiency. At the same time, each photovoltaic cell module 1 includes a plurality of electrically connected photovoltaic cell chips 11, and each photovoltaic cell module 1 is also electrically connected, so that it can simultaneously receive light for power generation.

Each part of the solar cell system 100 of the present disclosure is described in detail below:

As shown in FIG. 1, the number of photovoltaic cell modules 1 is multiple. Each photovoltaic cell module 1 may include multiple photovoltaic cell chips 11. The photovoltaic cell chip 11 may be a gallium arsenide photovoltaic cell (GaAs cell). In the case, it can improve the photoelectric conversion efficiency and increase the power generation. Of course, the photovoltaic cell chip 11 may also be another photovoltaic cell or a device having a photovoltaic power generation function.

As shown in FIGS. 4 and 5, each photovoltaic cell chip 11 has a positive electrode and a negative electrode. In the same photovoltaic cell module 1, each photovoltaic cell chip 11 can be overlapped in order, that is, arranged in a line, and two adjacent photovoltaic cells are arranged. The chips 11 are overlapped, and two adjacent photovoltaic cell chips 11 can be electrically connected through a conductive material 12. At the same time, each photovoltaic cell chip 11 of the same photovoltaic cell module 1 is connected in series. For example, the positive electrode of one photovoltaic cell chip 11 is connected to the negative electrode of an adjacent photovoltaic cell chip 11. The conductive material 12 may be silver. When connecting, a positive electrode or a negative electrode of one photovoltaic cell chip 11 may be coated with silver paste and then connected to another photovoltaic cell chip 11. Coating of silver paste can be achieved by automated equipment to improve work efficiency.

As shown in FIG. 1, the number of photovoltaic cell chips 11 of each photovoltaic cell module 1 is the same, and multiple photovoltaic cell modules 1 can be arranged side by side. Two adjacent photovoltaic cell modules 1 can be spaced 1 mm apart, and of course, they can be smaller or larger than 1 mm. . A plurality of photovoltaic cell modules 1 may be connected in parallel through conductive connecting members 13 so as to generate power independently, and the conductive connecting members 13 may be bus bars or other connecting members.

As shown in FIG. 2 and FIG. 3, at least one of the first encapsulation layer 2 and the second encapsulation layer 3 is a high-blocking composite water-blocking film, and the high-blocking composite water-blocking film may be formed on a flexible polymer substrate by using an evaporation device. The formed inorganic thin film or nitride thin film, such as a PVDC coating film or an EVOH composite film, etc., of course, may also be other films, as long as it can play the role of light transmission and water blocking. Meanwhile, the first encapsulation layer 2 and the second encapsulation layer 3 may have a single-layer or multi-layer structure, and at least one of them has a thickness of 0.05 mm. Of course, the thickness may be less than 0.05 mm or greater than 0.05 mm. For example, the first encapsulation layer 2 and the second encapsulation layer 3 are both high-barrier composite water-blocking films, and both have a thickness of 0.05 mm.

The first encapsulation layer 2 and the second encapsulation layer 3 may be disposed facing each other, and each photovoltaic cell module 1 may be located between the first encapsulation layer 2 and the second encapsulation layer 3, and the first encapsulation layer 2 and the second encapsulation layer 3 may be After lamination, the photovoltaic cell module 1 is encapsulated between the first encapsulation layer 2 and the second encapsulation layer 3. As shown in FIG. 3, FIG. 3 is a pressed solar cell system 100. The first encapsulation layer 2 and the second encapsulation layer 3 are bonded together. The photovoltaic cell module 1 is located between the first encapsulation layer 2 and the second encapsulation layer 3. between.

As shown in FIG. 2, the solar cell system 100 according to the embodiment of the present disclosure may further include a first adhesive layer 4 and a second adhesive layer 5, and of course, a necessary adhesive film. The first adhesive layer 4 may be provided. Between the first encapsulation layer 2 and the photovoltaic cell module 1, a second adhesive layer 5 may be provided between the second encapsulation layer 3 and the photovoltaic cell module 1. Both the first adhesive layer 4 and the second adhesive layer 5 may be PO adhesive films, but it is not limited thereto, and may also be POE adhesive films or other adhesive films, so that the first encapsulating layer 2 and the second encapsulating layer 3 Adhesion to photovoltaic cell module 1.

It should be noted that, since the first adhesive layer 4 and the second adhesive layer 5 become thin during the lamination process, the first adhesive layer 4 and the second adhesive layer 5 are not shown in FIG. 3.

In one embodiment, the solar cell system 100 may include a photovoltaic cell module 1, a first encapsulating layer 2, a second encapsulating layer 3, a first adhesive layer 4, and a second adhesive layer 5. The first adhesive layer 4 may It is provided between the first encapsulation layer 2 and the photovoltaic cell module 1, and the second adhesive layer 5 may be provided between the second encapsulation layer 3 and the photovoltaic cell module 1. The photovoltaic cell module 1 includes a plurality of GaAs cells. Both the first encapsulating layer 2 and the second encapsulating layer 3 are 0.05 mm thick high barrier composite water blocking films, and the first adhesive layer 4 and the second adhesive layer 5 are 0.1. The mmPO film is formed after lamination, which can meet the requirements of drones, and has a power-to-weight ratio of less than 2 grams per watt.

As shown in FIG. 8, the solar cell system 100 according to the embodiment of the present disclosure may have a light receiving side and a backlight side. The light receiving side may be a side for each photovoltaic cell chip 11 for receiving sunlight, and the backlight side may be the photovoltaic cell chip 11 facing away. Sunny side. The solar battery system 100 may further include a back plate 6. The back plate 6 may be disposed on the backlight side of the solar battery system 100, and the back plate 6 may be an insulating film or a glass sheet, so as to block the backlight side of the solar battery system 100. When the solar cell system 100 is installed, the back plate 6 can be connected to the skin 2001 of the wing section.

An embodiment of the present disclosure provides a wing. As shown in FIG. 6 and FIG. 7, the wing 200 may include a plurality of wing segments, and each wing segment may be installed with at least one of the above-mentioned solar cell systems 100, wherein:

As shown in FIGS. 6 and 7, the number of wing segments may be multiple and assembled into a wing 200. For example, the wing 200 includes three wing segments, including a first wing segment 201 and a second wing segment 202. And third wing segment 203, where:

The first wing segment 201 may be fixed to the fuselage of the aircraft, and after being fixed to the fuselage, it extends symmetrically to both sides of the fuselage. The second wing section 202 is detachably connected to one end of the first wing section 201, the third wing section 203 is detachably connected to the other end of the first wing section 201, and the second wing section 202 and the third wing section 203 are about The first wing section 201 is arranged symmetrically.

Of course, the number of wing segments of the wing 200 may also be one, two, four or more, as long as it can form the wing 200, which is not particularly limited herein.

As shown in FIG. 6 and FIG. 7, a solar cell system 100 may be provided on each wing segment, and the number and size of the solar cell systems 100 on each wing segment may depend on the shape and size of the wing segment, and The number and size of the solar cell systems 100 on different wing sections may be the same or different.

For example: as shown in FIG. 6 and FIG. 7, a first solar cell system 101 is provided on the first wing section 201, a second solar cell system 102 is provided on the second wing section 202, and a third wing section 203 is provided. There is a third solar cell system 103. The second solar cell system 102 and the third solar cell system 103 are symmetrical with respect to the first wing segment 201, and the first solar cell system 101 is symmetrically disposed with respect to the center axis of the first wing segment 201. At the same time, the number of the first solar cell system 101, the second wing section 202, and the third solar cell system 103 may be multiple, but the number, shape, and size may be different. Each of the first solar cell systems 101 may be installed in parallel, series, or separated; each of the second solar cell systems 102 may be installed in parallel, series, or separated; each of the third solar cell systems 103 may be installed in parallel, series, or separated.

Since the wing of the embodiment of the present disclosure adopts the solar cell system 100 described above, the solar cell system 100 that matches each wing segment can be manufactured in advance, and then the solar cell system 100 is installed on the corresponding wing segment to avoid one by one installation. The photovoltaic cell chip is easy to install and operate, which improves the installation efficiency.

The following describes how the solar cell system 100 is connected to the wing segment:

As shown in FIG. 8, each wing segment may include a skin 2001. The material of the skin 2001 may be a fiber-resin composite material, but is not limited thereto, and may also be balsa wood, aluminum metal, carbon fiber resin composite material, and glass fiber. Resin composite materials, Kevlar fiber resin composite materials, basalt fiber resin composite materials, etc. The materials of the skin 2001 are not specifically limited here. The solar cell system 100 can be fixed to the skin 2001 by means of bonding, snapping, or the like. For example:

In one embodiment, the solar cell system 100 can be coated with epoxy adhesive to form an adhesive layer 7, and the adhesive layer 7 can be adhered to the surface of the skin 2001 so as to bond the solar cell system. 100 is bonded to the wing section. Of course, the adhesive layer 7 may be formed using an adhesive other than an epoxy adhesive, as long as the solar cell system 100 can be adhered to the surface of the skin 2001.

In another embodiment, the skin 2001 of each wing segment may be provided with a receiving groove, and the receiving groove is integrally formed when the skin 2001 is manufactured. The solar cell system 100 can be cooperatively disposed in the accommodating tanks. Each accommodating tank can be provided with a plurality of solar cell systems 100. The backlight side of each solar cell system 100 can be connected to the accommodating tanks with an adhesive such as epoxy glue. The inner wall of the solar cell is bonded, so that the solar cell system 100 is fixed in the accommodating groove. At the same time, the light receiving side of the solar cell system 100 may be flush with the surface of the skin 2001, and of course, it may be higher or lower than the surface of the skin.

In still another embodiment, the skin 2001 of each wing segment may be provided with an accommodation groove, and the solar cell system 100 may be cooperatively disposed in the accommodation groove and engaged with the inner wall of the accommodation groove. The inner wall defines the position of the solar cell system 100. For example, when manufacturing the skin 2001 through a mold, the solar cell system 100 can be directly placed in the mold of the skin 2001 to form the skin 2001 embedded with the solar cell system 100, which is free from bonding with an adhesive. . Of course, it is also possible to form a skin with an accommodation groove first, and then engage the solar cell system 100 in the accommodation groove, as long as the solar cell system 100 can be prevented from coming loose.

In other embodiments of the present disclosure, the solar cell system can be fixed to the skin 2001 in other ways, for example, the solar cell system is fixed to the skin 2001 through a special bracket, which will not be enumerated here.

In addition, the wing 200 according to the embodiment of the present disclosure may further include a skeleton, and the skeleton may be placed in the skin 2001 to support the skin 2001. Of course, the wing 200 may further include other components, which will not be described in detail here.

An embodiment of the present disclosure also provides an aircraft. The aircraft may be a fixed-wing aircraft, such as a fixed-wing drone, and of course, it may also be a manned fixed-wing aircraft.

As shown in FIG. 9, the aircraft may include the wing 200 of any one of the foregoing embodiments. For a specific structure of the wing 200, refer to the foregoing embodiment of the wing 200, and details are not described herein again. For the beneficial effects of the aircraft, reference may be made to the wing 200 and the solar cell system 100 described above, which will not be described in detail here. At the same time, the aircraft may further include a fuselage 300, and the wing 200 may be fixed to the fuselage 300. For example, the first wing segment 201 may be fixed to the fuselage 300 and symmetrically disposed about the center axis of the fuselage 300.

An embodiment of the present disclosure provides a manufacturing method of an airfoil. As shown in FIG. 10, the manufacturing method may include:

Step S110, providing a solar cell system and a skin, the solar cell system is a solar cell system in any embodiment of the present disclosure;

Step S120: bonding the solar cell system to the surface of the skin by an adhesive;

Step S130: placing the skin to which the solar cell system is adhered, in a vacuum chamber;

Step S140: The interior of the vacuum chamber is heated to cure the adhesive.

Each step is described in detail below:

In step S110, the skin may be formed by a special mold through a process such as extrusion or injection molding, which is not particularly limited herein. Solar cell systems can be made in advance.

In step S120, the adhesive may be epoxy glue or other adhesives. When bonding, the adhesive may be applied on the backlight side of the solar cell system to form an adhesive layer 7, and then the backlight The sides are bonded to the skin. For example, an epoxy adhesive may be coated on a side of the back sheet 6 away from the photovoltaic cell module 1 of the solar cell system to form an adhesive layer 7, and then the back sheet 6 is adhered to the surface of the skin.

In step S130, the vacuum chamber may be a space in a vacuum bag, and the vacuum bag has an opening that can be opened or closed. Of course, it can also be a closed space surrounded by a hard shell. For example, the skin to which the solar cell system is adhered can be placed in the vacuum bag and sealed.

In step S140, a heating device may be used to heat the interior of the vacuum chamber to cure the adhesive, thereby fixing the solar cell system to the surface of the skin. The structure of the heating device is not particularly limited as long as it can be used for heating.

An embodiment of the present disclosure also provides a method for manufacturing an airfoil. As shown in FIG. 11, the method may include:

Step S110: Provide a mold and a solar cell system, the solar cell system is a solar cell system in any embodiment of the present disclosure;

Step S120, a filler is built into the mold;

Step S130: Use the mold to form a skin through a molding process;

Step S140: removing the filler to form a receiving groove;

Step S150, the solar cell system is adhered to the accommodating groove by an adhesive;

Step S160, placing the skin to which the solar cell system is adhered, in a vacuum chamber;

Step S170: heating the inside of the vacuum chamber to cure the adhesive.

Each step is described in detail below:

In step S110, the structure of the mold may depend on the shape and size of the skin, and the skin may be formed by using the mold through processes such as extrusion or injection molding. Solar cell systems can be made in advance.

In step S120, the shape and size of the filler can be matched with the solar cell system to be installed on the skin, and the material of the filler can be a PET (polyethylene terephthalate) film material. Of course, Other materials are also possible.

In step S130, when forming the skin, the filling member may be placed in a mold, so that the filling member may be embedded in the finished skin, and the position of the filling member may be the same as the position where the solar cell system is to be installed. At the same time, when the filler is placed in the mold, a release agent may be applied to remove the filler from the finished skin.

In step S140, the filling member in the skin is removed to form an accommodating groove, and the accommodating groove can be placed or filled in the solar cell system.

In step S150, the solar cell system can be fitted into the receiving tank in a cooperative manner, and the solar cell system can be bonded to the inner wall of the receiving tank by an epoxy adhesive. When bonding, the adhesive can be applied to the backlight side of the solar cell system to form an adhesive layer, and then the solar cell system is placed in the containing groove and bonded to the bottom of the containing groove. For example, epoxy adhesive can be coated on the side of the back plate 6 away from the photovoltaic cell module 11 of the solar cell system, and then the solar cell system is placed in the containing groove to make the back plate 6 adhere to the bottom of the containing groove.

In step S160, the vacuum chamber may be a space in a vacuum bag, and the vacuum bag has an opening that can be opened or closed. Of course, it can also be a closed space surrounded by a hard shell. For example, the solar cell system and the skin can be placed in the vacuum bag and sealed.

In step S170, a heating device may be used to heat the interior of the vacuum chamber to cure the adhesive, thereby fixing the solar cell system to the surface of the skin. The structure of the heating device is not particularly limited as long as it can be used for heating.

An embodiment of the present disclosure also provides a method for manufacturing an airfoil. As shown in FIG. 12, the method may include:

Step S120, the solar cell system is built into the mold;

Step S130: Use the mold to form a skin through a molding process, and the skin exposes the solar cell system.

Each step is described in detail below:

For step S110, reference may be made to step S110 in the above manufacturing method, and details are not described herein again.

In step S120, the solar cell system may be placed in a mold, and a specific position thereof may be determined in advance according to a position on the skin where the solar cell system needs to be installed.

In step S130, a mold provided with a solar cell system can be used to form a skin by extrusion or injection molding, and the skin embedded with the solar cell system can be directly formed. This eliminates the need to separately install the solar cell system and improves work efficiency . At the same time, the skin exposes the solar cell system to ensure that the light receiving side of the solar cell system can normally receive sunlight.

Those skilled in the art will readily contemplate other embodiments of the present disclosure after considering the specification and practicing the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that conform to the general principles of this disclosure and include the common general knowledge or conventional technical means in the technical field not disclosed by this disclosure. . It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.

Claims

A solar cell system, characterized in that the solar cell system includes:

First encapsulation layer;

A second encapsulation layer disposed opposite to the first encapsulation layer;

One or more photovoltaic cell modules are sandwiched between the first encapsulation layer and the second encapsulation layer, and each of the photovoltaic cell modules is electrically connected, and each of the photovoltaic cell modules includes a plurality of electrical connections Photovoltaic cell chip.
The solar cell system according to claim 1, wherein the photovoltaic cell chip is a gallium arsenide photovoltaic cell.
The solar cell system according to claim 1, wherein each of the photovoltaic cell chips in the same photovoltaic cell module is sequentially overlapped, and two adjacent photovoltaic cell chips are connected by a conductive material.
The solar cell system according to claim 1, wherein at least one of the first encapsulation layer and the second encapsulation layer is a high barrier composite water blocking film.
The solar cell system according to claim 1, wherein each of the photovoltaic cell modules is connected in parallel, and each photovoltaic cell chip of the same photovoltaic cell module is connected in series.
A wing includes at least one wing section, wherein each of the wing sections is installed with at least one solar cell system according to any one of claims 1-5.
The wing of claim 6, wherein the wing segment comprises:

Skin, the solar cell system is adhered to the surface of the skin by an adhesive.
The wing of claim 6, wherein the wing segment comprises:

The skin is provided with an accommodating groove, and the solar cell system is cooperatively disposed in the accommodating groove, and is snapped or bonded to the inner wall of the accommodating groove.
The airfoil according to claim 6, wherein the number of the wing segments is plural and includes:

First wing segment

A second wing segment detachably connected to one end of the first wing segment;

The third wing segment is detachably connected to the other end of the first wing segment, and is disposed symmetrically with the second wing segment with respect to the first wing segment.
A method for manufacturing an airfoil, which is characterized by comprising:

Providing a solar cell system and a skin, the solar cell system being the solar cell system according to any one of claims 1-5;

Bonding the solar cell system to a surface of the skin through an adhesive;

Placing the skin to which the solar cell system is adhered in a vacuum chamber;

The inside of the vacuum chamber is heated to cure the adhesive.
A method for manufacturing an airfoil, which is characterized by comprising:

Providing a mold and a solar cell system, the solar cell system is the solar cell system according to any one of claims 1-5;

Inserting a filler into the mold;

Forming a skin by a molding process using the mold;

Removing the filler to form an accommodation groove;

Bonding the solar cell system into the containing groove through an adhesive;

Placing the skin to which the solar cell system is adhered in a vacuum chamber;

The inside of the vacuum chamber is heated to cure the adhesive.
A method for manufacturing an airfoil, which is characterized by comprising:

Providing a mold and a solar cell system, the solar cell system is the solar cell system according to any one of claims 1-5;

Inserting the solar cell system into the mold;

A skin is formed by a molding process using the mold, and the skin exposes the solar cell system.
An aircraft, comprising the wing according to any one of claims 6-9.