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A scissor linkage type annular space deployable antenna mechanism

A circular space and linkage technology, applied in antennas, folded antennas, electrical components, etc., can solve the problems of complex structure, poor rigidity, and heavy weight of loop antennas, and achieve weight and material cost reduction, high structural rigidity, and high density small effect

Active Publication Date: 2018-10-02
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problems of complex structure, heavy weight and poor rigidity of existing loop antennas, the present invention further proposes a scissors linkage type circular space expandable antenna mechanism

Method used

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  • A scissor linkage type annular space deployable antenna mechanism
  • A scissor linkage type annular space deployable antenna mechanism
  • A scissor linkage type annular space deployable antenna mechanism

Examples

Experimental program
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Effect test

specific Embodiment approach 1

[0025] Specific implementation mode one: combine Figure 1 to Figure 12 To illustrate, a scissors-linked annular space expandable antenna mechanism described in this embodiment includes an outer ring 1, an inner ring 2 and a plurality of ropes 3, and ropes 3 are evenly arranged between the outer ring 1 and the inner ring 2, and the outer ring 1 includes a plurality of outer ring mechanisms connected end to end in sequence, each outer ring mechanism includes a vertical rod 4 and two side rods 5, the two side rods 5 are arranged in parallel, and a vertical rod 4 is arranged on two Between the side bars 5, between the side bars 5 and the vertical bars 4, between the vertical bars 4 and the vertical bars 4, and between the side bars 5 and the side bars 5 are all provided with ropes 3, and the inner ring 2 includes a plurality of inner ring mechanisms , a plurality of inner ring mechanisms are connected end to end in sequence, each inner ring mechanism includes scissors 6 and a ver...

specific Embodiment approach 2

[0030] Specific implementation mode two: combination Figure 1 to Figure 6 and Figure 10 to Figure 12 Note that the side bar 5 in this embodiment includes a side bar hinge 7, an elastic hinge 14 and two side links 13, the two side links 13 are connected by the elastic hinge 14, and the side bar hinge 7 is arranged on two adjacent outer bars. Between the ring mechanisms, one end of the side bar hinge 7 is rotatably connected to a side link 13 in an outer ring mechanism, and the other end of the side bar hinge 7 is rotatably connected to another side link 13 in the adjacent outer ring mechanism, The vertical rods 4 are respectively vertically affixed to the two side rod hinges 7 in the same outer ring mechanism. Other compositions and connection methods are the same as those in Embodiment 1.

[0031] When the side bar 5 is folded, the elastic hinge 14 bends to generate elastic force, so that the side link 13 has a tendency to extend and rotate outwards, providing power for th...

specific Embodiment approach 3

[0033] Specific implementation mode three: combination Figure 1 to Figure 9 Explain that the scissors 6 in this embodiment include a scissors hinge 8, two long connecting rods 10, two torsion springs 11 and four short connecting rods 9, and the middle parts of the two long connecting rods 10 cross through the scissors hinge 8 Set, the two ends of each long connecting rod 10 are respectively connected with a short connecting rod 9, between the long connecting rod 10 and the short connecting rod 9 are rotationally connected, the two ends of one of the long connecting rod 10 and the short connecting rod 9 A torsion spring 11 is provided, and the two short connecting rods 9 on one side are rotatably connected to the vertical bar hinges 12 respectively, and the short connecting rods 9 on the other side are respectively rotatably connected to the adjacent vertical bar hinges 12 . Other compositions and connection modes are the same as those in Embodiment 1 or 2.

[0034] The verti...

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Abstract

The invention provides a shear fork coordinated type annular space deployable antenna mechanism, relates to an aerospace antenna, particularly relates to the shear fork coordinated type annular space deployable antenna mechanism, and aims at solving the problems of complex structure, high weight and poor rigid intensity of the existing annular antenna. The shear fork coordinated type annular space deployable antenna mechanism comprises an external ring, an internal ring and multiple ropes. The ropes are arranged between the external ring and the internal ring. The external ring comprises multiple external ring mechanisms. Each external ring mechanism comprises a vertical rod and two side rods. The vertical rod is arranged between the two side rods. The ropes are arranged between the side rod and the vertical rod, the vertical rods and the side rods. The internal ring comprises multiple internal ring mechanisms. Each internal ring mechanism comprises a shear fork and a vertical rod hinge. The shear fork is connected with the middle part of the vertical rod through the vertical rod hinge. When the antenna mechanism folds, the external ring and the internal ring retract to form a cylindrical shape. When the antenna mechanism unfolds, the external ring and the internal ring unfold to form a double-ring shape. The shear fork coordinated type annular space deployable antenna mechanism is used for aerospace communication.

Description

technical field [0001] The invention relates to an aerospace space antenna, in particular to a scissors linkage type annular space expandable antenna mechanism. Background technique [0002] With the needs of communication, space science, earth observation and national defense construction, the demand for large space antennas in various countries is becoming more and more urgent. When the size of the antenna exceeds the range that the launch vehicle fairing (or space shuttle) can accommodate, the structural form of the deployable antenna must be used. During the launch phase, these large antennas must be folded, and after the spacecraft enters the predetermined orbit, it will be unfolded by the drive to become a working state. Compared with other satellite deployable antennas, the ring truss deployable antenna has a wide range of applications, a large antenna diameter (up to hundreds of meters), a simple topological structure, and a topological configuration that does not c...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H01Q15/18H01Q1/08
CPCH01Q1/08H01Q15/18
Inventor 郭宏伟邓宗全刘荣强黄勇李冰岩
Owner HARBIN INST OF TECH
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