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Rope tied nano satellite system for space debris capturing

A space debris and tethering technology, which is applied in the directions of space navigation equipment, tools, transportation and packaging, can solve problems such as collision and energy exchange, failure of capture missions, and damage to the capture mechanism of spacecraft, and achieve economic benefits. High, the effect of preventing the target from escaping

Active Publication Date: 2017-07-25
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the capture of non-cooperative targets, traditional methods such as flying net capture and robotic arm capture face the problem of collision and energy exchange during capture, which can easily cause damage to the capture spacecraft or capture mechanism, resulting in the failure of the capture task

Method used

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  • Rope tied nano satellite system for space debris capturing
  • Rope tied nano satellite system for space debris capturing
  • Rope tied nano satellite system for space debris capturing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0042] Such as image 3 As shown, it is a tether 3 with a hook and loop function, and the front and back double-sided tape-shaped hook and loop buttons are pasted on the front and back sides of the tether 3 respectively; bonding, such as Figure 4 As shown, after the tether 3 wraps around the space debris 4, the front hook and the back hook of the tether 3 contact and overlap each other. The bonding strength is related to the bonding material and buckle structure, the degree of compression during bonding, and the area of ​​the bonding area.

Embodiment 2

[0044] Such as Figure 5As shown, it is a tether 3 with a magnetic attraction function. The tether 3 is a warp-knitted hollow-core tether. Beads 32 and NdFeB magnetic beads 32 have the same magnetic poles facing each other (black and white are two magnetic poles in the figure). Preferably, the middle section 33 of the rope is hollow so as to prevent the ferromagnetic core wire 31 from colliding with the high temperature resistant NdFeB magnets during storage. The beads 32 are entangled; when the tether 3 is in the storage state, the magnetic poles of the same name between the NdFeB magnetic beads 32 repel each other to avoid mutual attraction, such as Figure 6 As shown, when the tether 3 completes the winding of the space debris 4, the ferromagnetic core wire segment 31 and the NdFeB magnetic bead 32 segment of the tether 3 provide the attraction force between the ropes to attract and overlap each other.

Embodiment 3

[0046] Such as Figure 7 , 8 As shown, it is a tether 3 with a shape memory function. The tether 3 is made of a superelastic material, which can be beryllium bronze or carbon fiber, so that it forms a helical wrapping structure with a radius of curvature in a free state. ;Such as Figure 9 As shown, when the tether 3 completes wrapping around the space debris 4 , the space debris 4 will be wrapped up by virtue of the holding force of the helical wrapping structure of the radius of curvature of the tether 3 . The tether 3 is received at the end of the nanostar 2 before the launch of the nanostar 2 .

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Abstract

The invention discloses a rope tied nano satellite system for space debris capturing. The rope tied nano satellite system comprises a launching platform, two nano satellites and a tying rope. The launching platform is used for carrying the two nano satellites and launching the two nano satellites towards space debris during space debris capturing. A buffering material is attached to the surface of each nano satellite. The two ends of the tying rope are separately connected with the two nano satellites. The tying rope is contained in the launching platform before the two nano satellites are launched and is unfolded and winds or encases the space debris to capture the space debris under traction of the nano satellites after the two nano satellites are launched. The rope tied nano satellite system has the advantages that the rope tied nano satellite system is adopted to capture the targets, and the targets in any shape can be captured through the flexible tying rope; and the nano satellites are provided with buffering materials, and the situation that the nano satellites and the targets are damaged due to collision between the nano satellites and the targets can be avoided; the tying rope has a bonding and buckling function, a magnetic attraction function, a shape memory function and an automatic tightening function, and the targets can be prevented from escaping; and compared with other capturing modes, the rope tied nano satellite capturing system has higher economic benefits.

Description

technical field [0001] The invention relates to the technical field of capturing and recovering space debris, in particular to a tethered nanosatellite system for capturing space debris. Background technique [0002] With the development of the aerospace industry, the number of spacecraft in space is also increasing, and consequently, the number of failed or malfunctioning spacecraft is also increasing. These spacecraft occupy valuable orbital resources and pose a threat to the normal operation of spacecraft; at the same time, the non-faulty components on these spacecraft have very important economic value, which makes the recovery of these failed or malfunctioning spacecraft very special. Significant. Due to the high difficulty of space debris cleanup, the space debris cleanup is currently in the conceptual design stage, including flying net capture, robotic arm capture and other methods. [0003] Considering that space debris is mostly scrapped spacecraft, malfunctioning...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G4/00
CPCB64G4/00
Inventor 宋婷袁建平武海雷张宪亮孙玥
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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