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A step-by-step flexible solar cell array

A flexible solar cell and array technology, which can be used in spaceflight equipment, spaceflight aircraft, transportation and packaging, etc., and can solve the problems of spacecraft orbit change and low fundamental frequency of flexible solar cell arrays.

Active Publication Date: 2021-09-07
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Problems to be solved by the present invention: overcome the deficiencies of the prior art, provide a flexible solar cell array that can be deployed step by step, solve the problem that the flexible solar cell array can only be deployed at a fixed length when entering orbit, and the fundamental frequency of the flexible solar cell array is too high. Attitude control problems that lead to spacecraft orbit change and docking

Method used

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  • A step-by-step flexible solar cell array
  • A step-by-step flexible solar cell array
  • A step-by-step flexible solar cell array

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Embodiment Construction

[0031] The present invention will be further described in detail below with reference to the accompanying drawings.

[0032] figure 1, figure 2 , image 3 Is a structural diagram of present invention provide a stepwise deployment of the solar array flexible. As shown in FIG. A stepwise deployment of the flexible solar array comprising: a storage tank 1, the storage box 2, the tensioning mechanism 3, the guide mechanism 4, the pressing release mechanism 5, 6 composed of a plurality of flexible solar panel flexible solar panel array, the second unlocking device 7. The flexible solar panel array is divided into a first step portion and a second step flared portion expanded; Step expanded section is provided, a second step to expand the flexible portion 6 of the solar panel, respectively the number N1, N2, and N1 and N2 are odd; secondary unlocking device 7 positioned between the first step expand block 6 N1 N2 and flexible solar panels deployed second step portion. A storage box locat...

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Abstract

The invention relates to a step-by-step flexible solar battery array. The flexible solar cell array is composed of an upper storage box, a lower storage box, a tensioning mechanism, a guiding mechanism, a compression release mechanism, a flexible solar panel, and a secondary unlocking device. As the power generation device of the spacecraft, the flexible solar cell array can withstand the mechanical environment of the launch section of the spacecraft. With the cooperation of the external deployment mechanism, it has the power to maintain two kinds of deployment lengths and structural rigidity, and at the same time meets the requirements of the initial stage of the spacecraft entering orbit. The requirements for the base frequency of the solar cell array in the orbit and docking stages and the demand for the power generation of the solar cell array in long-term orbital operation.

Description

Technical field [0001] The present invention relates to the field of spacecraft solar array technology, provides a particularly flexible solar array deployment isolable step. Background technique [0002] The flexible solar cell has a characteristic of unfolding length and a low base frequency, and the spacecraft is attarable to the spacecraft in its unfolded state, especially the milestive, and the attitude control is very difficult. Therefore, if the flexible solar battery array can perform only the first step in the spacecraft, only the first step is completely unfolded, so that the flexible solar cell is shorterly unfolded and the high base frequency to meet spacecraft attitude control requirements. In the mile, the second step is performed after the second step is completely expanded to satisfy the spacecraft power generation, and the current flexible solar cell array can be solved with the contradiction between the base frequency and the spacecraft or the stations. [0003]...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/44B64G1/22
CPCB64G1/222B64G1/443
Inventor 倪啸枫程雷霍杰咸奎成付清山王治易张雷
Owner SHANGHAI AEROSPACE SYST ENG INST
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