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Fan-shaped solar wing repetitive folding and unfolding mechanism

A folding mechanism and the technology of the sun, applied in the field of aerospace, can solve problems such as disturbance and affecting the attitude stability of the spacecraft, and achieve the effects of increasing stability, saving envelope space, and positioning accurately

Active Publication Date: 2014-07-30
ZHEJIANG SCI-TECH UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the spacecraft performs orbit change or attitude adjustment control, the flutter of the deployed solar panels will disturb the posture of the spacecraft itself, affecting the attitude stability of the spacecraft

Method used

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  • Fan-shaped solar wing repetitive folding and unfolding mechanism
  • Fan-shaped solar wing repetitive folding and unfolding mechanism
  • Fan-shaped solar wing repetitive folding and unfolding mechanism

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Embodiment Construction

[0032] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0033] Such as figure 1 , 2-1As shown in and 2-2, a fan-shaped solar wing repeated folding mechanism includes a spacecraft body connecting frame 2, a stationary plate connecting frame 3, a solar wing support frame overall, a planetary wheel deployment mechanism 7, a synchronous belt transmission mechanism, and a trapezoidal lock release mechanism. Mechanism and motor 14; the solar wing supporting frame generally includes a supporting frame assembly 6, a moving guide plate 4 and a stationary plate 11; The walls are all slidingly connected, and are connected with the moving guide plate 4 and the stationary plate 11 through the planetary wheel expansion mechanism 7; one end of the stationary plate 11 is fixed to the side wall of the stationary plate connecting frame 3, and the two ends of the stationary plate connecting frame 3 are respectively locked wit...

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Abstract

The invention discloses a fan-shaped solar wing repetitive folding and unfolding mechanism. Most spacecrafts adopt a one-time unfolding locking mechanism, and thus the stability is influenced when the spacecrafts change an orbit or adjust and control the attitude. A supporting frame component is respectively connected with the inner wall of a movement guide plate, and the inner wall of a stationary plate; one end of the stationary plate is fixed with a stationary plate link span; two ends of the stationary plate link span are respectively hinged to a spacecraft body; a driven pulley and a driving pulley are connected by a conveyor belt; the other end of the stationary plate is hinged to the center of the driven pulley; the rim of the driven pulley is hinged to the one end of the movement guide plate; the movement guide plate is fixed with a wedge; two spring installation seats are fixed on the stationary plate; the inner side of each spring installation seat is connected with a clamping block through a locking-unlocking spring; the clamping block close to the spacecraft body is hinged to the stationary plate, and the other block is hinged to a locking-unlocking sliding block which is connected with the stationary plate in a sliding way. Repetitive folding and unfolding of a fan-shaped solar wing can be realized by means of the fan-shaped solar wing repetitive folding and unfolding mechanism.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and relates to a fan-shaped solar wing, in particular to a fan-shaped solar wing repeating folding mechanism. Background technique [0002] Solar wings are a major form of space power supply for spacecraft. At present, most spacecraft solar wings use rigid substrates, and their deployment often adopts a one-time deployment and locking mechanism, that is, the solar wings are folded and folded in the fairing during the launch phase, and they are unfolded and locked to the working state at one time after orbiting. Since the solar cell substrate is a rigid substrate, its weight and volume are relatively large, and corresponding requirements are put forward for the carrying space. When the spacecraft performs orbit change or attitude adjustment control, the flutter of the deployed solar panel itself will disturb the posture of the spacecraft body and affect the attitude stability of the spacecraft...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/44
Inventor 胡明李文娟陈文华撖亚頔邓红林王黎喆冯军
Owner ZHEJIANG SCI-TECH UNIV
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