Solar panel deployment limiting mechanism

A technology of solar cells and limiting mechanism, applied in the direction of power supply system of space navigation aircraft, can solve the problems of increasing the overall weight and use space, reducing product reliability, wasting resources and space, etc., and achieving light weight, easy assembly, and effective Good results

Active Publication Date: 2018-04-20
SHENYANG INST OF AUTOMATION - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing solar panel deployment mechanism is complicated in structure and large in size, which increases the overall weight and use space, wastes resources and space; and is difficult to assemble, and is easily affected by the environment during work, which reduces the reliability of the product

Method used

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Embodiment Construction

[0025] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0026] Such as Figure 1-7 As shown, the present invention includes a rotating shaft 1, a fixed hinge 3 and a movable hinge 6, wherein the movable hinge 6 is connected to the solar panel, and one side of the fixed hinge 3 and one side of the movable hinge 6 are provided with shaft holes respectively, and the movable hinge 6 The side connected to the rotating shaft 1 is provided with multiple mounting rings A10, and each mounting ring A10 is provided with a shaft hole A11; the side connecting the fixed hinge 3 with the rotating shaft 1 is provided with multiple groups, two for each group The mounting rings B12 are provided with shaft holes B13 on each mounting ring B12. Each mounting ring A10 is inserted between a group of two mounting rings B12, and the rotating shaft 1 passes through each shaft hole A11 and each shaft hole B13. Between the two outermost in...

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Abstract

The invention belongs to the field of solar panels and particularly relates to a solar panel deployment limiting mechanism. The solar panel deployment limiting mechanism comprises a rotating shaft, afixed hinge and a moving hinge. One side of the fixed hinge and one side of the moving hinge are provided with shaft holes respectively, and the rotating shaft penetrates the shaft holes in one side of the fixed hinge and the shaft holes in one side of the moving hinge to be connected with the fixed hinge and the moving hinge. Torsional springs sleeve the rotating shaft, a torsional spring arm atone end of each torsional spring is connected with the moving hinge while a torsional spring arm at the other end of each torsional spring is a free end, each free end is abutted against the fixed hinge after the moving hinge rotates around the rotating shaft to expand, and the fixed hinge and the moving hinge are provided with limiting bosses for limiting after deployment. The solar panel deployment limiting mechanism is easy in assembly, low in component quantity, simple in structure, light in weight, small in size and high in reliability.

Description

technical field [0001] The invention belongs to the field of solar battery sail panels, in particular to a solar battery sail panel deployment limiting mechanism. Background technique [0002] Most of the spacecraft use solar energy as the main energy source. In order to make the spacecraft work for a long time, it is necessary to unfold the solar panel. Therefore, the solar panel deployment mechanism is very important in the aerospace field. The existing solar panel deployment mechanism is complex in structure and large in size, which increases the overall weight and use space, wastes resources and space; moreover, it is difficult to assemble and is easily affected by the environment during work, which reduces the reliability of the product. Contents of the invention [0003] In view of the above-mentioned problems existing in the deployment of the solar battery sails of the existing spacecraft, the object of the present invention is to provide a limiting mechanism for th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/44
CPCB64G1/44Y02E10/50
Inventor 刘金国李江伟
Owner SHENYANG INST OF AUTOMATION - CHINESE ACAD OF SCI
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