Capture method of spacecraft capture system based on nozzle capture and star-rocket docking ring locking

A docking ring and spacecraft technology, which is applied to aerospace vehicles, aerospace vehicle docking devices, aircraft, etc., can solve the problems of poor versatility and adaptability of spacecraft capture systems, and achieve multiple reuse and economic benefits High, wide range of effects

Active Publication Date: 2022-03-04
HARBIN INST OF TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to solve the problem of poor versatility and adaptability of the spacecraft capture system. The present invention provides a spacecraft capture system based on nozzle capture and star-rocket docking ring locking

Method used

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  • Capture method of spacecraft capture system based on nozzle capture and star-rocket docking ring locking
  • Capture method of spacecraft capture system based on nozzle capture and star-rocket docking ring locking
  • Capture method of spacecraft capture system based on nozzle capture and star-rocket docking ring locking

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specific Embodiment

[0080] refer to image 3 The capture device 4 of this embodiment includes: an airbag storage mechanism 4-2, a locking airbag 4-3, a No. 1 global camera 4-4, three axial range finders 4-5, a buffer airbag 4-6, Transmission mechanism 4-7, gas supply system 4-8, three radial range finders 4-9, gas cylinder 4-10, attitude thruster 4-11, driving device 4-12, housing 4-13, propulsion Thrusters 4-14, controllers and docking devices 4-15.

[0081] Among them, the airbag storage mechanism 4-2 stores three locking airbags 4-3; the axial range finder 4-5 and the radial range finder 4-9 adopt a laser range finder; the attitude thruster 4-11 and the propulsion Thruster 4-14 adopts cold jet thruster.

[0082] Airbag storage mechanism 4-2, locking airbag 4-3, buffer airbag 4-6, transmission mechanism 4-7, air supply system 4-8, gas cylinder 4-10, driving device 4-12, housing 4- 13 form the airbag device;

[0083] The front end face of housing 4-13 is a conical surface, and buffer air bag...

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Abstract

In order to solve the problem of poor versatility and adaptability of the spacecraft capture system, the invention provides a spacecraft capture system based on nozzle capture and star-rocket docking ring locking, which relates to the technical field of non-cooperative spacecraft capture. The invention includes: a six-degree-of-freedom adjustment device, used to adjust the position and attitude of the locking device, so that the locking device contacts the docking surface of the docking ring of the star and rocket; a capturing device, used to detect the nozzle of the spacecraft Throat position, control the airbag to enter the throat of the spacecraft nozzle, inflate the airbag, use the airbag to lock the throat of the nozzle to achieve capture; the locking device, when the locking device contacts the docking surface of the star-arrow docking ring, It is used to radially lock the outer edge of the star arrow docking ring by using the locking part. The invention releases the capture device to the nozzle throat of the target, and captures the target nozzle; by recovering the capture device, the docking range from the capture device to the locking device is tightened; the locking device locks the star-arrow docking ring of the target through the locking component .

Description

technical field [0001] The invention relates to a spacecraft capture system, in particular to a spacecraft capture system based on nozzle capture and star-rocket docking ring locking, and relates to the technical field of non-cooperative spacecraft capture. Background technique [0002] After entering the 21st century, with the vigorous development of space technology, countries around the world are developing and exploring deep space more and more frequently, and space systems are becoming more and more complex. However, the risk of aerospace technology is very high. While bringing huge benefits, it will also cause huge losses due to spacecraft launch failure, orbital operation failure and limited life of spacecraft. Therefore, in order to minimize the loss caused by spacecraft failure or failure, it is necessary to carry out many researches on on-orbit service technology for space missions such as extending the life of spaceflight and removing orbital debris (such as aband...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/64
CPCB64G1/646
Inventor 刘延芳王旭齐乃明郭骁范庆玲袁秋帆谭新
Owner HARBIN INST OF TECH
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