Solar panel for space and method for manufacturing the same

• US 20020066828A1
• Filed: 12/04/2001
• Published: 06/06/2002
• Est. Priority Date: 12/05/2000
• Status: Active Grant

• Current Assignee: Sharp Kabushiki Kaisha (Hon Hai Precision Industry Co., Ltd.)
• Original Assignee: Sharp Kabushiki Kaisha (Hon Hai Precision Industry Co., Ltd.)
• Inventors: Hisamatsu, Tadashi, Kamimura, Kunio, Saga, Tatsuo, Nakamura, Kazuyo
• Granted Patent: US 6,799,742 B2
• Time in Patent Office: Days
• US Class Current: 244/173
• CPC Class Codes: B64G 1/443 Photovoltaic cell arrays
• CPC Class Codes: Y02E 10/52 PV systems with concentrators
• CPC Class Codes: Y10S 136/292 Space - satellite

Abstract

The object of the invention is to provide a solar panel and a method for manufacturing the same, wherein the manufacture of the solar panel for use in space and repair work thereon can be performed easily and in little time. An entirety of the solar panel is configured by detachably linking a plurality of unit solar cell modules, which include a plurality of solar cells and connection wires for connecting the solar cells, and electrically connecting the unit solar cellmodules to one another. Thus, a solar panel can be easily fabricated by combining standardized unit solar cellmodules. Moreover, by simply mechanically connecting the unit solar cell modules, they can be electrically connected, and thus the time necessary for manufacture or repair of solar panels can be shortened.

Claims

1. A solar panel for use in space comprising:

a plurality of unit solar cell modules including a plurality of solar cells and connection wires for connecting the solar cells,

wherein an entirety of the solar panel for use in space is configured by linking the plurality of unit solar cell modules and the linking of the unit solar cell modules electrically connects the unit solar cell modules to one another.

2. The solar panel for use in space of claim 1, wherein the unit solar cell modules are linked by detachable means.

3. The solar panel for use in space of claim 1, wherein a bypass diode for protecting the solar cells with respect to a reverse bias is installed in the unit solar cell modules.

4. The solar panel for use in space of claim 1, wherein the unit solar cell modules have a support plate with a honeycomb structure of which principal material is aluminum, and that the solar cells are fastened to this support plate.

5. The solar panel for use in space of claim 1, wherein the entire of the solar panel is configured by fitting the unit solar cell modules into accommodating spaces for accommodating the unit solar cell modules which are provided in a frame body.

6. The solar panel for use in space of claim 1, wherein the entirety of the solar panel is configured by arranging and linking together the unit solar cell modules on a substrate on which the arrangement positions for the unit solar cell modules are indicated.

7. The solar panel for use in space of claim 1, wherein the unit solar cell modules have a structure with which they can be mechanically linked to one another, and that the entirety of the solar panel is configured by mechanically linking the unit solar cell modules to one another.

8. The solar panel for use in space of claim 1, wherein the unit solar cell modules have a structure with which they can be mechanically linked to one another, and that an entirety of the panel is configured by fitting a plurality of mutually linked unit solar cell modules into a frame body provided with accommodating spaces for accommodating a plurality of mutually link ed unit solar cell modules.

9. The solar panel for use in space of claim 7, wherein the mechanical structure linking the unit solar cell modules to one another includes a protruding portion provided on one side of each of the unit solar cell modules and a recessed portion provided on another side of each of the unit solar cell modules.

10. The solar panel for use in space of claim 8, wherein the mechanical structure linking the unit solar cell modules to one another includes a protruding portion provided on one side of each of the unit solar cell modules and a recessed portion provided on another side of each of the unit solar cell modules.

11. The solar panel for use in space of claim 5, wherein the frame body includes ground conduction paths for electrically connecting a light receiving side surface of each of the unit solar cell modules to a spacecraft ground.

12. The solar panel for use in space of claim 8, wherein the frame body includes ground conduction paths for electrically connecting a light receiving side surface of each of the unit solar cell modules to a spacecraft ground.

13. The solar panel for use in space of claim 5, wherein a plurality of unit solar cell modules interconnected is lined with a resin film.

14. The solar panel for use in space of claim 6, wherein a plurality of unit solar cell modules interconnected is lined with a resin film.

15. The solar panel for use in space of claim 7, wherein a plurality of unit solar cell modules interconnected is lined with a resin film.

16. The solar panel for use in space of claim 8, wherein a plurality of unit solar cell modules interconnected is lined with a resin film.

17. The solar panel for use in space of claim 1, wherein the unit solar cell modules are provided with condenser lenses for gathering light into the solar cells.

18. The solar panel for use in space of claim 17, wherein the unit solar cell modules are provided with a frame for supporting the condenser lenses, the solar cells, and the connection wires.

19. The solar panel for use in space of claim 17, wherein the condenser lenses have a plurality of non-consecutive focal points with respect to a single lens plate, and that the solar cells are arranged at positions corresponding to those focal points.

20. The solar panel for use in space of claim 17, wherein the connection wires and a bypass diode for protecting the solar cells with respect to a reverse bias are disposed in regions which are not irradiated with light gathered by the condenser lenses.

21. The solar panel for use in space of claim 17, wherein a surface of the condenser lenses is coated with a light transmitting, conductive thin film that is connected to a spacecraft ground.

22. A method for manufacturing a solar panel for space use includes:

configuring an entirety of the solar panel for use in space by detachably linking a plurality of unit solar cell modules, which include a plurality of solar cells and connection wires for connecting the solar cells, connecting the unit solar cell modules to one another, and

repairing or adjusting the solar panel by removing and exchanging a portion of the linked unit solar cell modules.