CN218633851U

CN218633851U - Semi-flexible solar array device

Info

Publication number: CN218633851U
Application number: CN202223074778.6U
Authority: CN
Inventors: 项军华; 李洪峻; 邓辉; 黄秋柏; 易略
Original assignee: Zhangzhou Hangsheng Satellite Technology Co ltd
Current assignee: Zhangzhou Hangsheng Satellite Technology Co ltd
Priority date: 2022-11-18
Filing date: 2022-11-18
Publication date: 2023-03-14
Anticipated expiration: 2032-11-18

Abstract

The application relates to a semi-flexible solar array device. The semi-flexible solar array device comprises: at least one standard component, a semi-flexible substrate, a bus circuit, and a module landing zone; the standard assembly, the bus circuit and the module lap joint area are all arranged on the semi-flexible substrate; each standard component is electrically connected with the bus circuit; the bus circuit is electrically connected with an external device through the module overlapping area. By adopting the semi-flexible solar array device, the cost of commercial spaceflight can be reduced, and the device has the requirement of universality.

Description

Semi-flexible solar array device

Technical Field

The application relates to the technical field of solar cell arrays, in particular to a semi-flexible solar array device.

Background

Spacecraft solar arrays are generally composed of electrical circuits and structural parts. The traditional spacecraft battery array mainly adopts a product customization mode, and a solar battery array correspondingly matched with each spacecraft is designed according to the structure configuration and the energy requirement of each spacecraft. The traditional solar array for spaceflight has high development cost and poor universality, and cannot meet the requirements of cost control and universality of commercial spaceflight.

SUMMERY OF THE UTILITY MODEL

In view of the above, there is a need to provide a semi-flexible solar array device that can reduce the cost of commercial space flight and meet the requirement of versatility.

A semi-flexible solar array device comprising at least one standard cell, a semi-flexible substrate, a bus circuit, and a module lap zone; the standard component, the bus circuit and the module lap joint area are all arranged on the semi-flexible substrate; each standard component is electrically connected with the bus circuit; the bus circuit is electrically connected with an external device through the module lap joint area.

In one embodiment, the module comprises a plurality of solar cells, a bus bar, and a module lap zone; the plurality of solar cells are electrically connected with the bus branch through the lap joint area of the standard component; the bus branch is electrically connected with the bus circuit.

In one embodiment, the module further comprises a semi-flexible strip; and the standard component, the confluence branch and the overlapping area of the standard component are all arranged on the semi-flexible support plate.

In one embodiment, all of the semi-flexible support plates comprise a semi-flexible substrate.

In one embodiment, the module further comprises a universal mounting hole.

In one embodiment, the module, the bus circuit and the module landing zone are secured to the semi-flexible substrate by solder pads.

In one embodiment, the solar cell, the bus bar and the module overlapping region are fixed on the semi-flexible support plate through the welding pad.

In one embodiment, the module further comprises a plurality of cell tabs; the plurality of solar cells are connected in series and in parallel through the cell lap joint strips.

In one embodiment, the standard component lap zone comprises a positive component lap zone and a negative component lap zone.

The utility model has the advantages of as follows:

(1) The design and manufacturing process of the spacecraft battery array can be simplified, the technical state of the solar array module is unified, the work of identification test and the like is not required to be carried out in each application, the development period of the solar array can be effectively shortened, and the reliability of products can be improved;

(2) According to the method, the series-parallel connection relation of different standard components can be designed according to the energy requirements and the product line requirements of the spacecraft, and the development and production of diversified and coverable standard modules are realized;

(3) This application utilizes semi-flexible base plate to change in the integration to other structure surfaces to reduce the design requirement of solar array to other structures, compare with current spacecraft customization solar array, this application can dispose solar array wantonly according to the satellite demand, advantage such as with low costs, commonality and reliability height, suitable mass production.

(4) The method is suitable for modular design, simplifies the manufacturing process and is suitable for large-scale production.

Drawings

FIG. 1 is a schematic diagram of a semi-flexible solar array apparatus according to one embodiment;

FIG. 2 is a schematic diagram of a modular unit in one embodiment;

FIG. 3 is a schematic diagram illustrating electrical connections between solar cells according to one embodiment;

the module comprises a standard component 101, a semi-flexible substrate 201, a bus circuit 301, a module lap zone 401, a solar cell sheet 1011, a universal mounting hole 1012, a bus branch 1013, a positive component lap zone 1014, a negative component lap zone 1015 and a semi-flexible support plate 1016.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.

In one embodiment, as shown in fig. 1, a semi-flexible solar array apparatus is provided, the apparatus comprising at least one module 101, a semi-flexible substrate 201, a bus circuit 301, and a module lap zone 401; the standard cell 101, the bus circuit 301, and the module landing zone 401 are all disposed on the semi-flexible substrate 201; each module 101 is electrically connected to the bus circuit 301; the bus circuit 301 is electrically connected to an external device through the module overlapping region 401.

The utility model provides a above-mentioned semi-flexible solar array device, standard component 101, converge circuit 301 and module overlap area 401 and all set up on semi-flexible base plate 201, semi-flexible base plate 201 is standard component 101, it provides the structural support to converge circuit 301 and module overlap area 401, standard component 101 realizes the series-parallel connection through converging circuit 301 on base plate semi-flexible 201, finally assemble at module overlap area 401, realize the power output of semi-flexible solar array device, semi-flexible base plate changes in integratively to other structure surfaces, thereby reduce the design requirement of solar array to other structures, compare with current spacecraft customization solar array, this application can dispose solar array wantonly according to the satellite demand, and is with low costs and the commonality is high.

In one embodiment, the module 101 includes a plurality of solar cells 1011, a bus 1013, and a module lap zone; the plurality of solar cells are electrically connected with the bus branch through the overlapping area of the standard component; the bus branch is electrically connected with the bus circuit.

In an embodiment, as shown in fig. 2, the solar cell is a basic photoelectric conversion unit of a standard module, and the solar cell is electrically connected in the standard module through a bus bar 1013.

In one embodiment, the module 101 further includes a semi-flexible support 1016; the module 101, the bus branch 1013, and the module overlap region are all provided on a semi-flexible strip.

In one embodiment, all of the semi-flexible strips 1016 comprise the semi-flexible substrate 201.

In a specific embodiment, all the semi-flexible support plates are integrally formed or spliced or overlapped to form the semi-flexible substrate. According to standard component design parameters and voltage and current requirements, the size and the pad distribution of the semi-flexible substrate 201 are determined, and the semi-flexible support plate 1016 material can be FPC, PCE, PI and the like.

In one embodiment, the module further includes universal mounting holes 1012.

In a particular embodiment, the mounting holes provide a mechanical interface for the mounting of the module to the spacecraft structure.

In one embodiment, the module 101, the bus circuit 301, and the module landing zone 401 are secured to the semi-flexible substrate 201 by bonding pads.

In one embodiment, the solar cell 1011, the bus 1013 and the module landing zone are attached to the semi-flexible strip 1016 by solder pads.

In one embodiment, the module further comprises a plurality of cell tabs 1018; the plurality of solar cells 1011 are connected in series and in parallel through the cell lap joint 1018.

In one embodiment, the standard component lap zone comprises a positive component lap zone 1014 and a negative component lap zone 1015.

In a specific embodiment, as shown in fig. 3, the solar cells 1011 in the standard module 101 are electrically connected in sequence through the cell strap 1018, so as to realize series and parallel connection of the cells in the standard module, and finally converge to the positive electrode 1014 and the negative electrode 1015 in the inter-board overlapping region of the standard module, so as to realize an electrical interface between the standard module and the semi-flexible solar array device, and finally realize electrical connection and convergence in the semi-flexible solar array device through the convergence circuit 301.

The standard component 101 can modify the number of series-parallel connections according to the requirement so as to meet the requirements of different voltages and currents of the semi-flexible battery array module.

The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.

The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the utility model. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, and these are all within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.

Claims

1. A semi-flexible solar array apparatus, comprising at least one module, a semi-flexible substrate, a bus circuit, and a module lap zone; the standard assembly, the bus circuit and the module lap joint area are all arranged on the semi-flexible substrate; each standard component is electrically connected with the bus circuit; the bus circuit is electrically connected with an external device through the module overlapping area.

2. The semi-flexible solar array device according to claim 1, wherein the standard cell comprises a plurality of solar cells, a busbar, and a standard cell overlap region; the plurality of solar cells are electrically connected with the bus branch through the overlapping area of the standard component; the bus branch is electrically connected with the bus circuit.

3. The semi-flexible solar array apparatus of claim 2, wherein the standard assembly further comprises a semi-flexible strip; and the standard assembly, the confluence branch and the overlapping area of the standard assembly are all arranged on the semi-flexible support plate.

4. A semi-flexible solar array apparatus as claimed in claim 3 wherein all of the semi-flexible strips constitute a semi-flexible substrate.

5. The semi-flexible solar array apparatus according to claim 1, wherein the standard component further comprises a universal mounting hole.

6. The semi-flexible solar array apparatus of claim 1, wherein the standard cell, the bus circuit, and the module landing zone are secured to the semi-flexible substrate by bonding pads.

7. The semi-flexible solar array apparatus according to claim 3, wherein the solar cell panels, the bus bars and the module landing zones are secured to the semi-flexible support sheet by solder pads.

8. The semi-flexible solar array apparatus of claim 4, wherein the module further comprises a plurality of cell tabs; and the solar cells are connected in series and parallel through the cell lap joint strips.

9. The semi-flexible solar array apparatus of claim 3, wherein the standard component lap zones comprise a positive component lap zone and a negative component lap zone.