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Swing suppression method for tether recovery of failure satellite

A technology of tethers and satellites, applied in the aerospace field, can solve problems such as system oscillation and instability, and achieve the effects of low cost, high efficiency, and strong operability

Active Publication Date: 2021-04-02
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem of system oscillation or even instability caused by the rope-retracting process of the tethered towing system, and to provide a swing suppression method for the recovery of the failed satellite tether

Method used

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  • Swing suppression method for tether recovery of failure satellite
  • Swing suppression method for tether recovery of failure satellite
  • Swing suppression method for tether recovery of failure satellite

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Embodiment 1

[0118] Assuming that the tethered drag system is located in a geosynchronous circular orbit with an orbital radius of 42164 km at the initial moment, the number of rope nodes in the bead chain model is 21. The pitch and yaw directions of the fragments at the time of capture each have an initial angular velocity of 5° / s. The tether recovery task needs to shrink the original length of 100m to 20m. Its system parameters are shown in the table below.

[0119] Table 1 Initial parameters of tethered towing system

[0120]

[0121] Step 1: launch the trailer spacecraft into orbit, and complete the capture of space debris;

[0122] Step 2: Establish an accurate model of the three-dimensional attitude-orbit coupling dynamics of the tethered drag system through the Newton-Euler method;

[0123] Step 3: Formulate a rope-retracting strategy;

[0124] A variable number of knot points is used to simulate the change of the tether during reeling. As the winch rotates, the original len...

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Abstract

The invention aims to solve the problem that a tether recovery excitation system vibrates after a failure satellite is captured, and provides a swing suppression method for tether recovery of the failure satellite. After the failure satellite is captured by the rope net, the failure satellite, the tugboat and the tether form a tethered towing system. A tether dragging system fine model in a three-dimensional space is established, a tether is composed of a series of bead points formed by connecting springs and dampers in series, and the change of the tether in the tether winding process is simulated by reducing the number of the bead points and changing parameters of a tail end tether section. For the flexible spacecraft system, a feedback fluctuation control method is provided, and swing of the system is effectively restrained by absorbing waves returned to a tugboat. Feedback fluctuation control can drag the failure satellite while the tether is recovered, attitude and orbit integrated control is achieved, the system is rapidly stabilized after the tether is recovered, and the clearing task is completed.

Description

technical field [0001] The invention relates to a tether dragging stability control method, in particular to a tether dragging and retrieving rope swing suppression method for a failed spacecraft, which is suitable for the space debris removal process and belongs to the aerospace technology field. Background technique [0002] Since the launch of the first artificial earth satellite in 1957, as of the end of 2016, humans have carried out more than 5,000 spacecraft launches, sending more than 6,700 spacecraft into Earth orbit, and only nearly 1,400 of all launched spacecraft One spacecraft is effectively in service, while others have become nonfunctional and turned into space junk. More than 260 in-orbit spacecraft or rocket disintegration / explosion / impact (broken) events produced a large number of space junk, which confirmed the Kessler phenomenon. With the rapid development of ultra-large-scale low-orbit constellations of companies such as SpaceX and oneweb, near-Earth spa...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/17G06F30/20B64G1/66B64G4/00G06F111/10G06F119/14
CPCG06F30/15G06F30/17G06F30/20B64G1/66B64G4/00G06F2111/10G06F2119/14
Inventor 祁瑞姚傅祯汤亮
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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