Flexible solar cell module and preparation method and application thereof

Abstract

The invention discloses a flexible solar cell module and a preparation method and application thereof. The flexible solar cell module comprises a package skin and a module framework, wherein the module framework is arranged on a surface of the package skin, and the package skin outwards extend along at least one edge of the module framework to form a cladding edge. The flexible solar cell is prepared by a hot pressing integrated package process. The flexible crystalline silicon solar cell module has the following advantages of high surface attachment, excellent surface aerodynamic performance, light weight and the like, is convenient to install and has wide application in a spacecraft such as a solar powered unmanned air vehicle.

Description

technical field [0001] The invention belongs to the technical field of solar cells, and in particular relates to a flexible solar cell component for space, a preparation method and application thereof. Background technique [0002] High-altitude and long-endurance solar-powered drones have the advantages of high flight altitude, long working hours, wide coverage, flexible use, low operating costs, and no environmental pollution. The platform has a very broad application prospect. It uses solar radiation energy as power to continuously fly unmanned aerial vehicles at high altitudes for long periods of time. It uses photovoltaic cells to convert solar energy into electrical energy, and drives propellers to rotate through electric motors to generate flight power. During the day, solar-powered UAVs rely on solar cells laid on the surface of the body to convert absorbed solar radiation into electrical energy, maintain the operation of the power system, avionics and payloads, and...

AI Technical Summary

Problems solved by technology

Traditional rigid solar cell modules generally use PET light-transmitting film (about 200 μm thick) + EVA layer (about 500 μm thick) + monocrystalline silicon wafer or polycrystalline silicon wafer (about 180 μm thick) + TPE backlight, and its surface density is usually 2.0~ 2.5 kg / m 2 , leading to the lack of flexibility of the solar cell module, not only cannot adapt to the fit with the airfoil surface, but also has a large mass, which reduces the load of the solar aircraft and is difficult to meet the application requirements of the solar aircraft

[0004] At present, in the disclosed solar cell module manufacturing technology for solar drones, such as CN203659894 U and CN201510680597, rigid solar cells are used to prepare solar cell components. Fragmentation, components cannot undergo large bending deformation, and it is difficult to adapt to the fit of large curvature changes on the wing

Moreover, the laying and installation process of the solar cell module and the wing frame in these patents is complicated, and the installation structure is difficult to meet the high smoothness of the wing surface required by the aerodynamics of the UAV.

In addition, as in the CN203659894 U patent, although the area density of the traditional solar cell module is reduced by more than 35%, the area density still reaches 1.2Kg / m 2 At the same time, the solar cell modules prepared in this patent lack a flexible support substrate, which makes it difficult to ensure the commonality between the solar cell modules and the UAV wing frame and the reliability of the solar cells

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