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Preparation method of solar cell module applied to near-space aircraft

A technology for solar cell components and adjacent spaces, which is applied in the direction of electrical components, semiconductor devices, circuits, etc., and can solve the problems of junction box weight, weather resistance and flatness, solar cell array weight, surface flatness restrictions, and resistance to shading Inappropriate methods and other issues, to achieve the effect of ensuring energy demand and reliability requirements, ensuring the flatness of the light-receiving surface, and avoiding irreversible damage

Pending Publication Date: 2021-02-26
中电科蓝天科技股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Therefore, it is obviously not applicable to use the anti-shading method in ground photovoltaics
In addition, considering the load capacity and aerodynamic efficiency of the near-space vehicle, the weight of the solar cell array and the flatness of the surface are strictly limited. Require

Method used

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  • Preparation method of solar cell module applied to near-space aircraft
  • Preparation method of solar cell module applied to near-space aircraft

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Embodiment Construction

[0030] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in combination with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are exemplary only, and are not intended to limit the scope of the present invention. Also, in the following description, descriptions of well-known structures and techniques are omitted to avoid unnecessarily obscuring the concept of the present invention.

[0031] Such as Figure 1-2 , in the embodiment of the present application, the present invention provides a method for preparing a solar cell module applied to a space vehicle, the method includes the steps of:

[0032] Prepare the first and second stacks;

[0033] aligning solar cells 1 on the first stack;

[0034] A diode 5 is correspondingly placed next to each of the solar cells 1;

[0035] welding ribbon 4 on the...

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Abstract

The invention discloses a preparation method of a solar cell module applied to a near-space aircraft. The method comprises the steps: preparing a first lamination layer and a second lamination layer;orderly arranging solar cells on the first lamination layer; correspondingly arranging a diode beside each solar cell; welding a welding strip on a positive electrode main grid of each solar cell; connecting the first end of the solder strip with a negative electrode of the corresponding diode; connecting the second end of the solder strip with a positive electrode of the corresponding diode and the negative electrode of the next adjacent solar cell; placing the second lamination layer on all the solar cells to obtain a solar cell module; laminating the solar cell module; and cutting the solarcell module. According to the preparation method, the diodes are added at the serial gaps of battery strings, so that the technical problem that the diodes cannot be added on each single battery of atraditional monocrystalline silicon series solar battery is solved.

Description

technical field [0001] The invention belongs to the technical field of near-space vehicles, and in particular relates to a method for preparing a solar cell module applied to near-space vehicles. Background technique [0002] At present, the main source of energy for near-space vehicles (including solar-powered drones, airships, and aerostats, etc.) is solar energy. The working principle of the solar cell array used in near space is to convert solar energy into electric energy for use by various equipment on the aircraft. In order to make better use of solar power for power supply, the solar cell array is generally arranged on the upper surface of the aircraft that is not blocked by the structure. However, Some mission loads will inevitably be installed on the upper surface of the wing, such as antennas, etc.; or the aircraft will be affected by the external environment during the ground joint test or ascent process, and some near-space vehicles, such as overpressure balls, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01L31/18H01L31/048H01L31/044
CPCH01L31/18H01L31/048H01L31/044Y02E10/50Y02P70/50
Inventor 张丹红呼文韬李钏孙国瑞
Owner 中电科蓝天科技股份有限公司
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