Space electrostatic protection solar cell array interconnection package structure and method

Abstract

The present invention discloses a space electrostatic protection solar cell interconnection package structure and a method. The space electrostatic protection solar cell interconnection package structure disclosed by the invention comprises a substrate, solar cells and anti-radiation conductive glass cover sheets; the surface of the substrate is coated with a layer of high-resistance conductive adhesive; the solar cells are bonded onto the surface of the substrate; one missing corner of each solar cell is connected in parallel with a bypass diode; the conductive layers of the anti-radiation conductive glass cover sheets are far away from the solar cells and cover the surfaces of the solar cells; the upper surface, lower surface and corresponding side surfaces of one corner of each anti-radiation conductive glass cover sheet are plated with metal thin films; and the metal thin films are connected in series with the bypass diodes through the high-resistance conductive adhesive. The method of the invention is not only compatible with a traditional solar cell ray assembly process, but also is simple and reliable. With the method adopted, automatic assembly can be realized.

Description

Technical field

[0001] The invention relates to power supply technology in the aerospace field, in particular to a space static electricity protection solar cell array interconnection packaging structure and method. Background technique

[0002] With the development of space technology, space vehicles and sub-systems tend to be lighter, low energy consumption, multi-functional and complex load integration development. The high-voltage solar cell array has the advantages of low energy loss and less cable consumption, which has become an inevitable trend in the development of space power systems, and a large number of foreign aircraft have been widely used. However, due to the effects of the space environment, static electricity accumulation and secondary discharge will occur on the insulating surface of the solar cell array, resulting in damage to the battery array and the aircraft cannot continue to operate normally.

[0003] In order to overcome this shortcoming, 400~600V high v...

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