Solar panel unfolding system based on hot knife

A technology for solar panels and deployment systems, applied in the field of solar panels deployment systems, can solve the problems of large separation impact and large forbidden area of ​​solar wings, and achieve the effects of easy assembly, low cost and small impact

Active Publication Date: 2021-02-09
CHANGGUANG SATELLITE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention aims to solve the problems of relatively large separation impact and large forbidden area for solar wings in the existing mic

Method used

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  • Solar panel unfolding system based on hot knife
  • Solar panel unfolding system based on hot knife
  • Solar panel unfolding system based on hot knife

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specific Embodiment approach 1

[0036] Specific implementation mode one: combine Figure 1-12 Describe this embodiment, a solar panel deployment system based on a hot knife, which includes a satellite body 1 and sail panels 2 positioned on both sides of the satellite body 1,

[0037] It also includes a miniature hinge 3, a hot knife structure 4, a support base 5 and a strong horse line 6, and each sailboard 2 is connected to the satellite body 1 through a miniature hinge 3, and the sailboard 2 is pre-buried and pressed. The embedded part 7, the hot knife structure 4 is installed on the satellite body 1, and the two compression embedded parts 7 are connected by a strong horse line 6, and the hot knife structure 4 cuts the strong horse line 6 to realize the unfolding of the sailboard 2, At least one support seat 5 is provided between each sailboard 2 and the satellite body 1 , and each support seat 5 is fixedly connected to the satellite body 1 .

[0038] This application is used for the pressing release and ...

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Abstract

The invention discloses a solar panel unfolding system based on a hot knife, and belongs to the technical field of spacecraft solar panel unfolding and locking. According to the invention, the problems of large separation impact and large distribution forbidding area required by the solar wing in the existing compression release and expansion locking mode of the micro-nano satellite solar panel are solved. Each sailboard is connected with the satellite body through a micro hinge, a pressing embedded part is embedded in each sailboard, the hot knife structure is installed on the satellite body,the two pressing embedded parts are connected through a strong horse wire, and the unfolding of the sailboards is realized by cutting the strong horse wire through the hot knife structure. At least one supporting base is arranged between each sailboard and the satellite body, and each supporting base is fixedly connected with the satellite body. The system is used for compressing, releasing, unfolding and locking the micro-nano satellite solar panel. The system has the characteristics of low cost, simple structure, easiness in assembly, light weight, small impact, high piece distribution rate, easiness in standardization and modularization and the like.

Description

technical field [0001] The invention relates to a solar panel deployment system based on a hot knife, and belongs to the technical field of spacecraft solar panel deployment and locking. Background technique [0002] In recent years, with the rise of commercial aerospace, the development of technologies such as micro-devices and components, integrated multi-functional structures, space plug and play, and integrated integrated electronics have been widely used in micro-nano-satellites, giving micro-nano-satellites The design brings new opportunities and challenges. Micro-nano satellites are developing towards high integration and high functionality. The realization of various complex functions on satellites is inseparable from the supply of energy. Solar panels are an important part of the power subsystem. The components play a vital role in the entire life cycle of the satellite. Due to the small size of the micro-nano satellite, it is difficult to meet the energy demand of ...

Claims

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Application Information

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IPC IPC(8): B64G1/44
CPCB64G1/44
Inventor 赵相禹张道威赵春娟张雷谷松陈善搏高飞孙洪雨段胜文
Owner CHANGGUANG SATELLITE TECH CO LTD
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