Four-connecting-rod unfolded-structure flexible solar wing

A technology of four-bar linkage and deployment mechanism, applied in the aerospace field, can solve the problems of heavy weight and large folded envelope, and achieve the effects of light weight, reduced folded envelope, and insensitive gaps at joints

Active Publication Date: 2015-12-16
BEIJING INST OF SPACECRAFT SYST ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are disadvantages such as heavy weight and large folding envelope
[0003] In order to simultaneously realize the requirements of high power, small retraction envelope, and light weight, the traditional rigid and semi-rigid solar wings are difficult to meet the demand, and a new type of flexible solar wing is required

Method used

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  • Four-connecting-rod unfolded-structure flexible solar wing
  • Four-connecting-rod unfolded-structure flexible solar wing
  • Four-connecting-rod unfolded-structure flexible solar wing

Examples

Experimental program
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Effect test

Embodiment

[0041]In this embodiment, the unfolding mechanism 1 is in the form of a sleeve; the connection and separation device 5 is used to control the connection or disengagement of the lower end of the box plate assembly and the expansion mechanism 1; the connection and separation device 6 between the plates is used to control the upper box plate 3 and the lower box plate 2 connection or separation. The upper link a10 and the upper link b13 are connected by a hinge; the lower link a7 and the lower link b8 are connected by a spring hinge 9; the free end of the upper link b13 and the deployment mechanism 1 are connected by a top hinge 16 Connection; the free end of the upper link a10 is connected with the upper box plate 3 by the upper box plate link hinge 19; the free end of the lower link a7 is connected by the lower box plate link hinge 18 between the lower box plate 2; The free end of the connecting rod b8 is connected with the unfolding mechanism 1 by a lower box plate unfolding hi...

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PUM

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Abstract

The invention discloses a four-connecting-rod unfolded-structure flexible solar wing. In an unfolded state, connecting rods of the solar wing are used as two force members to serve as rigid supporting components for an upper box plate and a lower box plate. Thus, the beneficial effects of being light in weight and insensitive in joint gap are achieved. By means of a four-connecting-rod mechanism, the box plates are parallel to a main unfolded mechanism in a folded state, and the purpose of reducing folding envelopes is achieved. A belt spring mechanism is arranged in the connecting-rod mechanism to replace a traditional shaft pin type hinge, so that the beneficial effect of being light in weight is achieved. A quick locking mechanism is arranged in an upper connecting-rod mechanism, so that the upper box plate can form a triangular stable system after being unlocked. According to the four-connecting-rod unfolded-structure flexible solar wing, the scheme of spring driving and viscous damper speed reducing is utilized to replace the scheme of driving a hinge through a motor, so that the four-connecting-rod unfolded-structure flexible solar wing has the beneficial effects of being simple, reliable and light in weight. The locking mechanism is provided with allowance self-adapting design, so that the size deviation caused by processing errors and loaded transformation is compensated, and the normal functions are not affected.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a flexible solar wing in a four-link unfolded configuration, which is suitable for spacecraft with high requirements for retracting envelope and weight. Background technique [0002] With the development of my country's aerospace technology, the power demand of spacecraft is increasing rapidly. Flexible solar wings are generally used in occasions with a large deployment area, and their width and weight are generally relatively large, requiring high rigidity for deployment, and it is hoped that the folded envelope should be as small as possible. The traditional configuration adopts a series configuration: the box panels are connected to the main unfolding truss with large rigid hinges, and the box panels adopt a beam and panel configuration with a large cross-section. There are disadvantages such as heavy weight and large folding envelope. [0003] In order to simultaneously ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/44
Inventor 杨巧龙马静雅任守志王举梁世杰闫泽红
Owner BEIJING INST OF SPACECRAFT SYST ENG
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