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Integrated-type solar-wing supporting mechanism

A support mechanism and integrated technology, applied in the aerospace field, can solve problems such as non-coaxial jamming and complex structure of the support mechanism, and achieve the effect of improving the deployment stiffness, simple structure, and high reliability

Active Publication Date: 2018-07-27
CHANGGUANG SATELLITE TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem of complex structure of the support mechanism and easy occurrence of non-coaxial jamming, the present invention provides an integrated solar wing support mechanism

Method used

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  • Integrated-type solar-wing supporting mechanism
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  • Integrated-type solar-wing supporting mechanism

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Embodiment Construction

[0035] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0036] Such as figure 1 As shown, the solar wing 3 is connected with the satellite star body 1 through the deployment mechanism 2, and one end of the support mechanism 4 of the integrated solar wing support mechanism of the present invention is installed on the satellite star body 1 and the other end is installed on the solar wing 3, so as to improve the solar wing 3 Deployment stiffness, improve the fundamental frequency of optical satellite solar wing 3 deployment. The support mechanism 4 includes a star support seat 5, a first short support tube 6, a first seal ring 7, a first band spring 8, a second seal ring 9, a first long support tube 10, a third seal ring 11, a second Belt spring 12 , fourth seal ring 13 , second long support tube 14 , fifth seal ring 15 , third band spring 16 , sixth seal ring 17 , second short support tube and solar...

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Abstract

The invention relates to the technical field of spaceflight, in particular to an integrated-type solar-wing supporting mechanism. The problems that a supporting mechanism is complex in structure and prone to being subjected to non-coaxial jamming are solved. A satellite supporting seat, a first short supporting pipe, a first strip-shaped spring, a first long supporting pipe, a second strip-shapedspring, a second long supporting pipe, a third strip-shaped spring, a second short supporting pipe and a solar-wing supporting seat are glued sequentially. The satellite supporting seat is fixed to asatellite body, and the solar-wing supporting seat is fixed to a solar wing. The inner surfaces of the first strip-shaped spring, the second strip-shaped spring and the third strip-shaped spring are glued. The integrated-type solar-wing supporting mechanism further comprises six sealing rings which are glued on the outer surfaces of the two ends of the first strip-shaped spring, the second strip-shaped spring and the third strip-shaped spring in a one-to-one-correspondence mode. The number of structural parts of the supporting mechanism is small, the structure is simple, self-expanding and self-locking can be achieved, the non-coaxial jamming phenomenon is not prone to occurring when one or more supporting mechanisms are used simultaneously, the reliability is high, the expanding rigidityof the solar wing is improved, and the fundamental frequency of optical satellite solar wing expanding is increased.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to an integrated solar wing support mechanism. Background technique [0002] The foldable solar wings are folded on the satellite body in the launch state, and unfolded after the star rocket is separated. For high-resolution optical satellites, when the fundamental frequency of the solar wing deployment does not reach the specified value, its image resolution and attitude control accuracy will be seriously affected. In order to solve the problem of low fundamental frequency, a support mechanism is usually used to increase the deployment stiffness. However, when the supporting mechanism and the unfolding mechanism are deployed in space, it is very easy to cause non-coaxial jamming, which leads to the failure of the task, and the traditional supporting mechanism has a large number of structural parts. Contents of the invention [0003] In order to solve the problem of complex s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/44B64G1/22
CPCB64G1/222B64G1/443
Inventor 张道威侯燚红谷松谭陆洋辛建赵相禹
Owner CHANGGUANG SATELLITE TECH CO LTD
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