A torsion spring driven small satellite spaceborne deployable planar structure and its installation method

A plane structure, satellite technology, applied in the aerospace field, can solve the problem of not being very mature, and achieve the effects of simple production, high deployment reliability, high practical value and promotion value

Inactive Publication Date: 2017-01-11
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Generally, considering the limited volume of the satellite fairing of the launch vehicle and the limited energy that the small satellite can provide, the platform structure of the small satellite usually adopts the expandable structure and the potential energy stored in the folded state as the driving method, but there is no very Mature, or highly versatile technology, the market prospect in this field is promising

Method used

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  • A torsion spring driven small satellite spaceborne deployable planar structure and its installation method
  • A torsion spring driven small satellite spaceborne deployable planar structure and its installation method
  • A torsion spring driven small satellite spaceborne deployable planar structure and its installation method

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Embodiment Construction

[0044] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0045] Such as figure 1 , figure 2 , image 3 A torsion spring-driven small satellite on-board expandable planar structure 1 is shown, which is composed of basic equilateral triangle expansion units, which are driven by torsion springs 16 at nodes and can be used as a working platform for small satellites 2 . The main body of the expandable planar structure 1 carried by the small satellite is a thin-walled rod 5 , and also includes nodes, joints 11 , torsion springs 16 and pins 17 .

[0046] Such as Figure 5 As shown, the inner space of the thin-walled rod 5 is used to install the payload 18, and the two ends of the thin-walled rod 5 are respectively provided with riveting holes A3, and the thin-walled rod 5 is also provided with installation positioning holes 13 and walking holes. The wire hole 12, the installation positioning hole 13 is ...

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Abstract

The invention relates to the technical field of aviation and aims to provide a torsion spring driven moonlet borne expandable plane structure and a mounting method thereof. The torsion spring driven moonlet borne expandable plane structure comprises equilateral triangle unfolding units, wherein each equilateral triangle unfolding unit comprises a thin-walled rod member, a node, a connector, a torsion spring and a pin shaft; adjacent equilateral triangle unfolding units are spliced by using different nodes. The mounting method comprises the following steps of mounting effective load, connecting the thin-walled rod members with the connectors, connecting the thin-walled rod members with six-directional nodes, three-directional nodes, four-directional nodes, and center nodes, mounting two-directional nodes, welding a lead, connecting the moonlet borne expandable plane structure with a moonlet, and connecting a lead. The expandable plane structure is unfolded by the torsion springs at joints of the expandable plane structure and can be quickly switched into an unfolding state from a folding state, so that the expandable plane structure is simple in operation and high in expansion reliability.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a torsion spring-driven small satellite onboard expandable planar structure and an installation method thereof. Background technique [0002] In recent years, small satellites have been paid more and more attention due to their advantages of light weight, low cost and short research cycle. However, small satellites are light in weight, small in size, and have limited attitude control capabilities. Therefore, there are few working platforms on current small satellites, which limits the functions of small satellites. At present, small satellites mainly use small helical antennas to send and receive signals, and solar cells are pasted on the surface of the satellites to obtain energy, rather than relying on the antenna platform and solar sails on board. [0003] In order to expand the application field of small satellites, there is an urgent need for a larger platform structure ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10B64G1/22
Inventor 关富玲朱术华曹长明吴明儿张天昊帖拓马罡张振昌
Owner ZHEJIANG UNIV
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