Unfolding mechanism of flexible solar wing for space station

A technology for deploying mechanisms and space stations, which is applied in the aerospace field to achieve the effects of small footprint, increased rigidity, and wide application range

Active Publication Date: 2016-04-20
ZHEJIANG SCI-TECH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If a rigid solar array is used, the mass limitation becomes a prominent problem

Method used

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  • Unfolding mechanism of flexible solar wing for space station
  • Unfolding mechanism of flexible solar wing for space station
  • Unfolding mechanism of flexible solar wing for space station

Examples

Experimental program
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Embodiment Construction

[0026] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0027] Such as figure 1 , 2 As shown in and 3, a space station flexible solar wing deployment mechanism includes a bottom storage box 1, a storage cylinder body 2-1, a storage cylinder cover 2-2, an extension arm deployment mechanism 3, a top storage box 4, and a triangular prism extension arm 5 , Airfoil 6 and airfoil tensioning mechanism 7; Bottom storage box 1 is fixed with storage cylinder 2-1; Top storage box 4 is fixed with storage cylinder cover 2-2.

[0028] Such as Figure 4 As shown, the fixed frame 3-1 and the motor frame 3-4 of the extension arm expansion mechanism are fixed on the bottom of the storage cylinder 2-1; the motor 3-3 is fixed on the motor frame 3-4; the roller support shaft 3-6 passes through the bearing Supported on the fixed frame 3-1; the coupling 3-5 connects the output shaft of the motor 3-3 and the roller support shaft...

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PUM

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Abstract

The invention discloses an unfolding mechanism of a flexible solar wing for a space station. The quality limitation of rigid solar cell arrays becomes a prominent problem. The unfolding mechanism comprises a bottom storage box, a storage barrel body, a storage barrel lid, an extension arm unfolding mechanism, a top storage box, a triangular prism extension arm, an airfoil and an airfoil tensioning mechanism, wherein a bottom tripod of the triangular prism extension arm is fixedly connected with a boss in the storage barrel body, and the top tripod is fixedly connected with the barrel lid; the top storage box is fixedly connected with the storage barrel lid, and the bottom storage box is fixedly connected with the storage barrel body; the extension arm unfolding mechanism is fixed at the bottom of the storage barrel body and controls an extension arm to be unfolded at the constant speed; the airfoil tensioning mechanism is fixed in the top storage box, guarantees tension to a solar wing during unfolding, tensions the solar wing after unfolding and keeps certain rigidity. The solar wing is small in mass, the airfoil and the extension arm occupy small size after being folded, and the extension arm can be reliably locked after being unfolded.

Description

technical field [0001] The invention belongs to the technical field of aerospace, and in particular relates to a space station flexible solar wing deployment mechanism. Background technique [0002] The solar cell array is the main power supply device of the spacecraft. The solar cell array widely used at present is a folded solar cell array with a rigid substrate, also known as a solar wing. Because the spacecraft's demand for power far exceeds that of ordinary satellites, it needs a large area and can be loaded with foldable large solar wings in the launch vehicle to provide the main energy. If a rigid solar cell array is used, the mass limitation becomes a prominent problem. With the rapid development of aerospace technology, all countries have put forward higher requirements for the power supply of solar wings, requiring solar wings with light weight, larger folding ratio and reliable deployment and locking. Contents of the invention [0003] The purpose of the prese...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/44
CPCB64G1/443
Inventor 胡明陈超陈文华郑盛顾菲
Owner ZHEJIANG SCI-TECH UNIV
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