阅读说明：本技术 一种功能集成轻质太阳电池模块及其制备方法 (Function-integrated light solar cell module and preparation method thereof ) 是由 马宁华 徐建明 唐道远 蒋帅 王凯 周丽华 于 2021-08-25 设计创作，主要内容包括：本发明公开了一种功能集成轻质太阳电池模块及其制备方法,包含：太阳电池、柔性电路基板、平面天线、连接层、轻质结构框架；太阳电池固定连接在柔性电路基板的上表面,柔性电路基板的下表面与轻质结构框架固定,轻质结构框架的下表面还设有天线固定孔；轻质结构框架内设有绷弦网面,该绷弦网面由若干弦线编织构成；连接层包含若干个固定盘、弯曲环,固定盘粘贴在柔性电路基板的下表面,每个弯曲环连接两个相邻的固定盘；弦线穿过弯曲环,连接轻质结构框架和柔性电路基板。本发明通过轻质结构框架,实现太阳电池与平面天线的一体化复合,在不降低单个功能模块性能的情况下,显著降低整个飞行器件的重量和体积。(The invention discloses a function integrated light solar cell module and a preparation method thereof, wherein the method comprises the following steps: the solar cell comprises a solar cell, a flexible circuit substrate, a planar antenna, a connecting layer and a light structural frame; the solar cell is fixedly connected to the upper surface of the flexible circuit substrate, the lower surface of the flexible circuit substrate is fixed with the light structure frame, and the lower surface of the light structure frame is also provided with an antenna fixing hole; a string-stretching net surface is arranged in the light structure frame and is formed by weaving a plurality of strings; the connecting layer comprises a plurality of fixed disks and bending rings, the fixed disks are adhered to the lower surface of the flexible circuit substrate, and each bending ring is connected with two adjacent fixed disks; the strings are threaded through the flex ring to connect the lightweight structural frame and the flexible circuit substrate. According to the invention, the solar cell and the planar antenna are integrated and compounded through the light structural frame, and the weight and the volume of the whole flight device are obviously reduced under the condition of not reducing the performance of a single functional module.)

1. A function-integrated lightweight solar cell module, comprising: the solar cell comprises a solar cell, a flexible circuit substrate, a planar antenna, a connecting layer and a light structural frame;

the solar cell is fixedly connected to the upper surface of the flexible circuit substrate, the lower surface of the flexible circuit substrate is fixed with the light structure frame, and the lower surface of the light structure frame is also provided with an antenna fixing hole for fixing the planar antenna;

the light structure frame is internally provided with a string stretching net surface which is formed by weaving a plurality of strings;

the connecting layer comprises a plurality of fixed disks and bending rings, the fixed disks are adhered to the lower surface of the flexible circuit substrate, and each bending ring is connected with two adjacent fixed disks; the string passes through the bending ring to connect the lightweight structural frame and the flexible circuit substrate.

2. The functionally integrated lightweight solar cell module of claim 1, wherein: the four side walls of the light structure frame are provided with string stretching holes with the height in the same horizontal plane, and in the string stretching net surface, two ends of each string are fixed on the string stretching holes on two sides.

3. The functionally integrated lightweight solar cell module of claim 1, wherein: the flexible circuit substrate comprises: substrate material layers on the upper and lower surfaces and a circuit layer arranged inside; the circuit layer and the substrate material layer are adhered through the adhesive film.

4. The functionally integrated lightweight solar cell module of claim 3, wherein: the substrate material layer is made of a polyimide film.

5. The functionally integrated lightweight solar cell module of claim 4, wherein: the polyimide film is subjected to texturing treatment, wherein the texturing treatment is to improve the interface characteristic of the polyimide film and improve the adhesive force of the polyimide film to the fixed disk by plasma sputtering or chemical corrosion.

6. The functionally integrated lightweight solar cell module of claim 1, wherein: the light structural frame is a carbon fiber frame or a light aluminum alloy.

7. The functionally integrated lightweight solar cell module of claim 1, wherein said lightweight structural frame further comprises:

the mechanical interface is used for connecting other light structural frames to realize mechanical connection among the modules;

and the electrical interface is used for realizing the electrical connection between the modules.

8. The functionally integrated lightweight solar cell module of claim 1, wherein: and a thermal control layer is also arranged in the light structure frame to prevent the heat generated by the solar cell and the planar antenna from being mutually transferred to influence the performances of the solar cell and the planar antenna.

9. The functionally integrated lightweight solar cell module of claim 8, wherein: the side surface of the light structure frame is also provided with a plurality of thermal control fixing holes for fixing the thermal control layer.

10. A method of manufacturing a functionally integrated lightweight solar cell module according to any of claims 1 to 9, comprising:

s1, preparing a flexible circuit substrate;

s2, connecting the solar cells in series and parallel and then pasting the solar cells on the upper surface of the flexible circuit substrate;

s3, processing a light frame structure, and designing a plurality of string stretching holes and antenna fixing holes on the light frame structure;

s4, preparing a string stretching net surface, and enabling a plurality of strings to penetrate through the string stretching holes under uniform tension to form the string stretching net surface;

s5, mounting a connecting layer on the lower surface of the flexible circuit substrate, wherein the connecting layer comprises a plurality of fixed disks and bending rings, the fixed disks are adhered to the lower surface of the flexible circuit substrate, and each bending ring is connected with two adjacent fixed disks; after installation, a string passes through each bending ring;

and S6, fixing the plane antenna and the light structure frame through the antenna fixing hole.

Technical Field

The invention relates to the field of spacecraft energy systems, in particular to a function-integrated light solar cell module and a preparation method thereof.

Background

With the continuous promotion of space science and engineering, the performance requirements on each system of the space aircraft are higher and higher, and the weight of each system is required to be reduced as much as possible, so that the load ratio of the overall task is improved, and the launching cost of the aircraft is reduced. The solar cell array is the main energy source of the aircraft, and the output power of the solar cell array is in direct proportion to the illuminated area. The method solves the contradiction between the power demand of the aircraft on energy and the demand of the aircraft on volume and weight, and is the key point of the design attention of the solar power generation system of the spacecraft. The light weight technology, the function multiplexing technology and the like of the solar cell array can effectively utilize the space of the aircraft, reduce the volume and the weight of the whole aircraft, and are necessary ways for the technical development of the solar cell array.

The solar cell array and the planar antenna are large-area functional modules exposed outside on the aircraft, and the large-area antenna is compounded on the back surface of the solar cell, so that the area of the solar cell array is fully utilized, the size of the aircraft functional module is greatly reduced, and the volume and the weight of the whole aircraft are remarkably reduced. At present, a mode of directly embedding a planar antenna in a solar cell array for integration is adopted, so that the process difficulty is high, the working efficiency of the planar antenna is reduced, and meanwhile, the planar antenna and a feeder thereof damage and shield a solar cell structure, so that the power generation efficiency of the solar cell is reduced.

Disclosure of Invention

The invention aims to integrate and compound the solar cell and the planar antenna module without reducing the conversion efficiency of the solar cell array, thereby greatly reducing the total weight of the aircraft and reducing the design volume of the aircraft.

In order to achieve the above object, the present invention provides a function-integrated lightweight solar cell module, comprising: the solar cell comprises a solar cell, a flexible circuit substrate, a planar antenna, a connecting layer and a light structural frame;

the solar cell is fixedly connected to the upper surface of the flexible circuit substrate, the lower surface of the flexible circuit substrate is fixed with the light structure frame, and the lower surface of the light structure frame is also provided with an antenna fixing hole for fixing the planar antenna;

the light structure frame is internally provided with a string stretching net surface which is formed by weaving a plurality of strings;

the connecting layer comprises a plurality of fixed disks and bending rings, the fixed disks are adhered to the lower surface of the flexible circuit substrate, and each bending ring is connected with two adjacent fixed disks; the string passes through the bending ring to connect the lightweight structural frame and the flexible circuit substrate.

Preferably, the four side walls of the lightweight structural frame are provided with string stretching holes with the same height on the same horizontal plane, and two ends of each string in the string stretching net surface are fixed on the string stretching holes on two sides.

Preferably, the flexible circuit substrate includes: substrate material layers on the upper and lower surfaces and a circuit layer arranged inside; the circuit layer and the substrate material layer are adhered through the adhesive film.

Preferably, the substrate material layer is a polyimide film.

Preferably, the polyimide film is subjected to texturing, and the texturing is to improve the interface characteristic of the polyimide film by plasma sputtering or chemical etching, so as to improve the adhesion of the polyimide film to the fixed disk.

Preferably, the light structural frame is a carbon fiber frame or a light aluminum alloy.

Preferably, the lightweight structural frame is further provided with a plurality of: the mechanical interface is used for connecting other light structural frames to realize mechanical connection among the modules; and the electrical interface is used for realizing the electrical connection between the modules.

Preferably, a thermal control layer is further disposed in the lightweight structural frame to prevent heat generated by the solar cell and the planar antenna from being transferred to each other and affecting the performance of the solar cell and the planar antenna.

Preferably, the side surface of the light structure frame is also provided with a plurality of thermal control fixing holes for fixing the thermal control layer.

The invention also discloses a preparation method of the light solar cell module with the integrated functions, which comprises the following steps:

s1, preparing a flexible circuit substrate;

s2, connecting the solar cells in series and parallel and then pasting the solar cells on the upper surface of the flexible circuit substrate;

s3, processing a light frame structure, and designing a plurality of string stretching holes and antenna fixing holes on the light frame structure;

s4, preparing a string stretching net surface, and enabling a plurality of strings to penetrate through the string stretching holes under uniform tension to form the string stretching net surface;

s5, mounting a connecting layer on the lower surface of the flexible circuit substrate, wherein the connecting layer comprises a plurality of fixed disks and bending rings, the fixed disks are adhered to the lower surface of the flexible circuit substrate, and each bending ring is connected with two adjacent fixed disks; after installation, a string passes through each bending ring;

and S6, fixing the plane antenna and the light structure frame through the antenna fixing hole.

The technical effects of the invention comprise: the surface density of the function integrated solar cell module is greatly improved. The solar cell and the planar antenna are integrated and compounded through the light structural frame, and the weight and the volume of the whole flight device are obviously reduced under the condition that the performance of a single functional module is not reduced.

Drawings

FIG. 1 is a cross-sectional view of an integrated lightweight solar cell module structure of the present invention;

FIG. 2 is a schematic view of a tie layer of the present invention;

FIG. 3 is a schematic view of a strung bore and a thermal control fixing bore;

FIG. 4 is a bottom view of the lightweight structural frame;

FIG. 5 is a schematic view of the interfaces of the lightweight structural frame;

FIG. 6 is an assembled view of a lightweight structural frame;

FIG. 7 is a cross-sectional view of a structure of a flexible circuit substrate;

reference numerals: 1-a solar cell; 2-a flexible circuit substrate; 21-a welding window; 22-glue film; 23-a layer of substrate material; 24-a circuit layer; 3-stretching a string net surface; 4-a tie layer; 41-fixing disc; 42-a flex ring; 5-thermal control layer; 6-a planar antenna; 7-a lightweight structural frame; 71. 72-a mechanical interface; 73. 74-electrical interface; 75-antenna fixing holes; 76-string stretching holes; 77-thermally controlled fixed orifices.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inside", "outside", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in fig. 1, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; may be a mechanical connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The invention discloses a function-integrated light solar cell module structure, which comprises a solar cell 1, a flexible circuit substrate 2, a string-stretching net surface 3, a connecting layer 4, a planar antenna 6 and a light structure frame 7, as shown in figure 1. The string stretching net surface 3 is arranged in the light structure frame 7 and comprises a plurality of strings. After the solar cell 1 is designed in series-parallel connection, the solar cell 1 is fixed on the upper surface of the flexible circuit substrate 2, then the lower surface of the flexible circuit substrate 2 is fixedly connected with the light structure frame 7, the lower surface of the flexible circuit substrate 2 is also provided with a string stretching net surface 3 and a connecting layer 4 which are used for connecting the light structure frame 7 with the flexible circuit substrate 2, and the string stretching net surface 3 also plays a role in supporting the flexible circuit substrate 2 and preventing the flexible circuit substrate 2 from deforming.

As shown in fig. 2, the connection layer 4 includes a plurality of fixing disks 41 and bending rings 42, the bending rings 42 connect adjacent fixing disks 41, the fixing disks 41 are adhered to the lower surface of the flexible circuit substrate 2, and the string line passes through each bending ring 42.

As shown in fig. 3, a plurality of string stretching holes 76 are formed on four side surfaces of the lightweight structural frame 7, and the string stretching holes 76 are located at the same height; under the action of the thread drawing machine, two ends of a plurality of strings of the string stretching net surface 3 are fixed on string stretching holes 76 on two sides of the light structure frame 7, and the strings are made of high-strength fibers.

As shown in fig. 4, the lightweight structural frame 7 is also provided with antenna fixing holes 75 for fixing the planar antenna 6.

In some embodiments, as shown in fig. 1 and 3, a thermal control layer 5 is further laid in the lightweight structural frame 7 to prevent heat generated by the solar cell 1 and the planar antenna 6 from transferring to each other and affecting the performance of the solar cell 1 and the planar antenna 6. The light structure frame 7 is also provided with a thermal control fixing hole 77 for fixing the thermal control layer 5, and the thermal control fixing hole 77 is arranged below the string tightening hole 76.

In some embodiments, as shown in fig. 5 and 6, the side of the light structural frame 7 is further provided with mechanical interfaces 71 and 72 for connecting other light structural frames 7, so as to realize mechanical connection between modules; the lightweight structural frame 7 is also provided with electrical interfaces 73 and 74 for making electrical connections between the modules.

In some embodiments, as shown in fig. 7, in the flexible circuit substrate 2, the substrate material layer 23 is preferably a polyimide film, a circuit layer 24 is designed inside the substrate, and the circuit layer 24 is bonded to the polyimide film through an adhesive film 22. Then, carrying out hot press molding on the substrate material layer 23 and the circuit layer 24; presetting a welding window 21 for welding a battery string electrode; further, the surface of the substrate material layer 23 is textured by plasma sputtering or chemical etching for improving the adhesion of the substrate material layer 23 to the fixed disk 41.

The preparation method of the function-integrated light solar cell module structure is shown in the embodiment.

Examples

S1: and preparing a flexible circuit substrate. As shown in fig. 7, the circuit layer 24 of the solar cell is designed according to the requirement, in this example, the circuit layer 24 of the solar cell is a rolled copper foil with a thickness of 35 μm, a polyimide film is used as the substrate material layer 23 of the flexible circuit substrate 2, the thickness of the single-layer substrate material layer 23 is 25 μm, and the substrate material layer 23 and the circuit layer 24 are bonded through the adhesive film 22; further, the adhesive film 22 is an epoxy adhesive film; and the adhesive film 22, the substrate material layer 23 and the circuit layer 24 are hot-pressed to complete the composite preparation of the flexible circuit and the substrate. Texturing the surface of the substrate material layer 23 by plasma sputtering; then, a 9mm × 2mm circuit bonding window 21 is engraved on the surface of the flexible circuit substrate 2 by laser.

S2: and assembling the solar cell array, selecting the solar cell 1 according to design requirements, and carrying out series-parallel connection design on the solar cell array. Fixing the flexible circuit substrate 2 through a vacuum adsorption equipment platform, and sticking the solar cell 1 on the upper surface of the flexible circuit substrate 2 by using 704 silicon rubber;

s3: processing a light structure frame, as shown in fig. 3, 4, 5 and 6, selecting a carbon fiber structure frame for the light structure frame 7, and arranging a plurality of string stretching holes 76 on four side surfaces of the light structure frame 7 according to the size of batteries and the arrangement layout of the batteries, wherein the diameters of the string stretching holes 76 are 2 mm; a thermal control fixing hole 77 is arranged below the string tightening hole 76 and used for fixing the thermal control layer 5; an antenna fixing hole 75 is preset on the lower surface of the light structure frame 7; on the side of the lightweight structural frame 7 are preset a mechanical interface 71 and a mechanical interface 72, and an electrical interface 73 and an electrical interface 74.

S4: the string stretching net surface is prepared, in this example, glass fiber with the diameter of 0.9mm is selected as string, the glass fiber passes through the string stretching holes 76, and a string stretching machine is used for applying uniform tension of 6-8 pounds to each string, so that the string stretching net surface 3 with uniform tension is prepared.

S5: fixing and combining the lightweight battery array and the strung net surface, in the embodiment, a GD414 silicon rubber is used for sticking a fixed disc 41 in the connecting layer 4 and the lower surface of the flexible circuit substrate 2 together, and the fixed disc 41 is made of nickel alloy with the diameter of 4mm and the thickness of 0.1 mm; a bending ring 42 is arranged between every two adjacent fixed disks 41, a chord line passes through each bending ring 42, and the bending rings 42 are made of nickel wires with the diameter of 0.5mm and the length of 7.5 mm.

S6: laying a heat control layer, and laying a heat control layer 5 inside the light structure frame 7 and below the string stretching net surface 3; in this example, the thermal control layer 5 is a multi-layer polyimide.

S7: the planar antenna 6 and the light structural frame 7 are combined together through the antenna fixing hole 75, so that the solar cell 1 and the planar antenna 6 are combined integrally.

In summary, the light solar cell module structure with integrated functions can integrate the solar cell and the planar antenna in the same module, so that the volume required by the aircraft can be reduced; through the selection of the light frame structure and the flexible circuit substrate, the weight of the module can be reduced.

While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.