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A space debris derotation method based on space folding manipulator

A space debris and space folding technology, which is applied to aerospace equipment, transportation and packaging, tools, etc., can solve the problems of large energy consumption and time consumption, and achieve the effects of saving energy consumption, facilitating maneuvering, and saving space

Active Publication Date: 2022-06-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, for the capture of space manipulators, non-contact methods such as electromagnetic derotation and eddy current derotation are mainly used for derotation, which requires special structures such as coils on the end of the manipulator, and consumes a lot of energy and time

Method used

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  • A space debris derotation method based on space folding manipulator
  • A space debris derotation method based on space folding manipulator
  • A space debris derotation method based on space folding manipulator

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Embodiment Construction

[0047] In order to make the objectives, technical solutions and effects of the present invention clearer and clearer, the following examples are given to further describe the present invention in detail. It should be pointed out that the specific implementations described herein are only used to explain the present invention, but not to limit the present invention.

[0048] like figure 1 shown, figure 1 It is a schematic diagram of the model of the space robot platform and space debris. The two sides of the space robot platform body 1 are provided with solar panels 2. The space robot platform body is also provided with a number of nozzle groups 6. The front end is provided with a foldable robotic arm 3 and a robotic arm end device 4, and an adhesive layer 5 is arranged at the front end of the robotic arm end device. Catch space debris 7.

[0049] Attached now Figure 2-4 Describe a space debris racemization method based on the space folding mechanical arm of the present in...

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Abstract

The invention discloses a space debris derotation method based on a space folding mechanical arm, which is applied to a space robot platform in a predetermined orbit; the method of the invention is to firstly complete the approach to the space debris to be captured; and measure the rotation of the space debris Inertia spindle; use the end device with adhesive material to adhere and capture space debris; expand the foldable robotic arm to increase the distance between the space robot platform and space debris, and increase the moment of inertia of the entire assembly to perform derotation ; carry out further derotation by means of the air jet attitude control system on the space robot platform; finally tighten the mechanical arm to reclaim the space debris; the present invention can carry out safe contact derotation treatment on the space debris The force arm for derotation of jet force can be improved, and energy consumption can be reduced. The invention can be used for derotation and recovery of space debris, and can also be used for derotation and control of other rotating targets.

Description

technical field [0001] The invention relates to a space debris derotation method based on a space folding mechanical arm, which can be applied to the derotation and cleaning of tumbling space debris, and belongs to the space on-orbit service technology in the aerospace field. Background technique [0002] With the continuous increase of human exploration activities in outer space, while bringing huge benefits, it also has a continuous and far-reaching impact on the low-Earth orbit environment. For example, a large amount of space debris such as the last stage of rockets, abandoned satellites, and spacecraft collision derivatives poses a huge threat to the development of the aerospace industry in all countries in the world. A large amount of space debris is in a state of runaway for a long time, and is often affected by the perturbation torque such as gravity gradient, solar light pressure, and its own residual angular momentum before failure, which often causes extremely com...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G4/00
CPCB64G4/00B64G2004/005
Inventor 黄政文浩金栋平
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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