Overall isothermal solar cell array PCB substrate

Abstract

The invention provides an overall isothermal solar cell array PCB substrate, which comprises a composite substrate layer, copper layers covering the upper and lower surfaces of the composite substratelayer, and insulating layers covering the copper layers, wherein the composite substrate layer is formed by a combination of a multi-layer epoxy fiberglass fabric substrate and copper layers, and thefunction of the copper layers is heat conduction. The overall isothermal solar cell array PCB substrate has the beneficial effects of adopting a thermal control design method of integrating the copper layers inside the substrate, satisfying the requirements of a whole satellite on weight, reducing the temperature of solar cells so that the efficiency of converting optical energy into electric energy is increased, and satisfying requirements of the small satellite pair on energy.

Description

technical field [0001] The invention relates to a solar array PCB substrate, in particular to an overall isothermal solar cell array PCB substrate, which belongs to the field of aerospace technology. Background technique [0002] Satellites operate in the space environment, and the on-board energy mainly comes from batteries and solar energy. At present, spacecraft in space are mainly used to convert the sun's light energy into electrical energy through solar battery sails. Due to the increase in power consumption demand of spacecraft, the area of ​​sail panels is constantly increasing. The solar battery sails of conventional satellites are on both sides of spaceflight. Expanded, the substrate is pasted with semiconductor silicon wafers or gallium arsenide wafers, relying on them to convert the light energy of sunlight into electrical energy. [0003] Due to the high energy requirements of large satellites, the area of ​​the sail board increases, and the patch area of ​​the...

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Problems solved by technology

[0005] Large carbon fiber sailboards are used on conventional satellites, but for micro satellites, energy requirements are high, but weight and volume limitations make large carbon fiber boards unsuitable

The energy consumed is completely realized by the conversion of solar energy into electrical energy by satellite solar arrays. The disadvantage is that for small satellites, due to the small size and envelope size, the number of satellite solar arrays that small satellites can carry is limited. , the conversion of electric energy is small, and the requirements for volume and weight make the selection of sailboard substrates very important

[0006] The PCB substrate is light in weight, and the number of heating sheets pasted on the surface can meet the requirements of small satellites. Its disadvantage is that the horizontal and vertical thermal conductivity is very poor, which makes the heat more concentrated. Reduced capacity, affecting the energy demand of the entire star

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