A Space Flexible Arm Compression Release Mechanism for Fusible Link Unlocking

A release mechanism and flexible arm technology, applied in space navigation equipment, transportation and packaging, tools, etc., can solve the problems of limited strength and rigidity, damage, etc., and achieve the effect of simple structure, accurate preload, and convenient assembly and adjustment

Active Publication Date: 2022-02-08
HARBIN INST OF TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to its thin and long configuration, its strength and rigidity are limited. If it is not reliably pressed during launch, it will inevitably be damaged under the strong vibration and impact of the launch vehicle.

Method used

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  • A Space Flexible Arm Compression Release Mechanism for Fusible Link Unlocking
  • A Space Flexible Arm Compression Release Mechanism for Fusible Link Unlocking
  • A Space Flexible Arm Compression Release Mechanism for Fusible Link Unlocking

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] The fixed base 1 is connected to the satellite cabin board by screws, the cutter 2, the position detection micro switch 6, the limit micro switch 10, and the phenyl silicone rubber sheet 7 are connected to the fixed base 1 by screws, and the flexible arm 11 Place it in the cylindrical groove of the fixed base 1. One end of the compression cover plate 5 is connected to the fixed base 1 through a pin shaft 9, and a torsion spring 8 is installed in the middle of the pin shaft 9 to apply a torsional moment to the compression cover plate 5; The other end of cover plate 5 is equipped with stay cord 3 on it. The compression cover plate 5 is provided with a cylindrical groove, which adapts to the shape of the flexible arm, increases the contact area for compression, and makes the compression more reliable.

[0030] Before launching, the flexible arm 11 is placed in the cylindrical groove of the fixed base 1, and the position detection microswitch 6 can detect that the flexible...

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PUM

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Abstract

The invention provides a space flexible arm pressing and releasing mechanism for fuse unlocking, which belongs to the technical field of space flexible arm pressing and releasing mechanisms. The invention includes a fixed base, a fuse unlocking device, a pressing cover, a position detection micro switch, a phenyl silicone rubber sheet, a torsion spring, a pin shaft and a limit micro switch; before launching, adjust the position of the fuse unlocking device The locking device exerts an appropriate pre-tightening force on the pressing cover plate through the pull rope, so that the space flexible arm is pressed on the fixed base. After entering orbit, the ground sends a command to energize the cutter of the fuse unlocking device, and the resistance wire of the cutter heats up rapidly to fuse the pull rope. The present invention is reliable in compression, adopts the fusible wire unlocking device as the compression and unlocking tool, has a simple structure, can apply more accurate pre-tightening force, and is convenient for assembly and adjustment; there is no shock and vibration when unlocking, and can protect the space flexible arm from being damaged when launching. The damage caused by vibration and shock load is suitable for occasions where the locking force of the space flexible arm is not required.

Description

technical field [0001] The invention relates to a space flexible arm pressing and releasing mechanism for fuse unlocking, and belongs to the technical field of space flexible arm pressing and releasing mechanisms. Background technique [0002] The world launches an average of 80-130 satellites per year, but 2-3 satellites fail to enter orbit correctly, and 5-10 satellites correctly enter orbit, and 5-10 fail at the beginning of their life (the first 30 days after entering orbit) , which resulted in huge economic losses. For example, after my country's Xinnuo-2 satellite was launched on October 29, 2006, although the satellite's orbit was successfully determined, and the satellite's measurement and control, attitude and orbit control subsystems were in good condition, however, due to the solar sail The second deployment of the board and the deployment of the antenna were not completed, and the satellite could not work normally. This satellite, which cost 2 billion yuan and ha...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G4/00
CPCB64G4/00
Inventor 刘宇张彦连文康梁斌王学谦
Owner HARBIN INST OF TECH
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