Light low-cost substrate for moonlet solar battery array

A solar cell array, low-cost technology, applied in the direction of photovoltaic power generation, electrical components, photovoltaic module support structure, etc., to achieve the effects of avoiding cold welding, shortening development costs, and light weight

Inactive Publication Date: 2017-02-22
SHANGHAI SATELLITE ENG INST
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  • Abstract
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Problems solved by technology

The solar cell array for small satellites requires the characteristics of small envelope volume, light weight, simple structure, short processing cycle, and low manufacturi

Method used

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  • Light low-cost substrate for moonlet solar battery array
  • Light low-cost substrate for moonlet solar battery array

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Embodiment Construction

[0014] Several preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention is not limited to these embodiments. The present invention covers any alternatives, modifications, equivalent methods and schemes made on the spirit and scope of the present invention. In order to provide the public with a thorough understanding of the present invention, specific details are set forth in the following preferred embodiments of the present invention, but those skilled in the art can fully understand the present invention without the description of these details.

[0015] Such as Figure 1-Figure 2 As shown, the embodiment of the present invention provides a light-weight and low-cost substrate applied to a small satellite solar cell array. The substrate includes an aluminum honeycomb core 1, a carbon fiber composite grid panel 2, a polyimide film 3, and embedded beams 4. Compress the bushing 5 and ...

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Abstract

The invention discloses a light low-cost substrate for a moonlet solar battery array. The substrate comprises an aluminum honeycomb core, carbon fiber composite grid panels, a polyimide film, a built-in beam, a compressing liner and an embedded part, wherein the built-in beam is arranged in the aluminum honeycomb core along the direction of a connecting hinge; the built-in beam, the compressing liner and the embedded part are adhered to the interior of the aluminum honeycomb core through foam glue; the carbon fiber composite grid panels are respectively adhered to the front and rear sides of the aluminum honeycomb core; and the whole substrate is wrapped with the polyimide film through the glue and is once cured and formed. The solar battery array substrate has the characteristics of small enveloping volume, light weight, simple structure, short processing period, low manufacturing cost, and the like, and is the solar battery array substrate with higher application values in moonlets.

Description

technical field [0001] The invention relates to a spacecraft structure and mechanism, in particular to a light-weight and low-cost substrate applied to a small satellite solar cell array. Background technique [0002] With the development of aerospace technology, human beings have more and more needs for space exploration. Traditional large satellites have a long development cycle and high cost, which is difficult to meet intensive space exploration tasks; small satellites are low in cost and short in development cycle, especially suitable for scientific experiments. space exploration missions. The solar cell array for small satellites requires the characteristics of small envelope volume, light weight, simple structure, short processing cycle, and low manufacturing cost. The existing traditional solar cell array substrates for large satellites cannot meet the requirements and cannot be directly applied to small satellites. superior. Contents of the invention [0003] In...

Claims

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Application Information

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IPC IPC(8): H02S20/00
CPCH02S20/00Y02E10/50
Inventor 王萌周徐斌袁野王智磊薛景赛聂斌斌
Owner SHANGHAI SATELLITE ENG INST
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