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A tether drag derotation and deorbit method for a failed liquid-filled spacecraft

A liquid-filled spacecraft and tethering technology, applied in the aerospace field, can solve problems such as low cleaning efficiency

Active Publication Date: 2021-04-27
BEIJING INSTITUTE OF TECHNOLOGYGY +1
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  • Summary
  • 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 low cleaning efficiency in the existing space debris cleaning process, and to provide a tether drag derotation and de-orbit method for a failed liquid-filled spacecraft

Method used

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  • A tether drag derotation and deorbit method for a failed liquid-filled spacecraft
  • A tether drag derotation and deorbit method for a failed liquid-filled spacecraft
  • A tether drag derotation and deorbit method for a failed liquid-filled spacecraft

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Embodiment 1

[0073] There are many space debris in space, and the space debris gathers near the geosynchronous orbit. In order to remove a defunct satellite with remaining fuel, a maneuverable tugboat captures the defunct satellite, and then uses a tethered derotation and deorbiting method of a defunct fluid-filled spacecraft to tow the defunct satellite to Earth Grave orbit at an altitude of 300km above the synchronous orbit.

[0074] A tether drag derotation and de-orbit method for a failed liquid-filled spacecraft, comprising the following steps:

[0075] Step 1: Using the equatorial orbit elements, derive the orbital perturbation equation, and obtain the earth center distance R, orbital angular velocity ω, and orbital angular acceleration ε

[0076] The present invention uses the equatorial orbit element (semi-major axis p, f, g, h, k and longitude L), and the equatorial orbit element can use classical orbit elements (semi-major axis a, eccentricity e, inclination i, ascending node eq...

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Abstract

The purpose of the present invention is to solve the problem of low cleaning efficiency in the existing space debris cleaning process, and provide a tether drag derotation and de-orbiting method for a failed liquid-filled spacecraft. This method utilizes the tethered dragging system, considers the characteristics of liquid sloshing and flexible ropes, establishes a system model in three-dimensional space, and designs an attitude-orbit integration control method for this system. While stabilizing the attitude of the debris, it can effectively drag the space debris with fuel stably to the predetermined orbit, and can efficiently remove large space debris with remaining fuel in space.

Description

technical field [0001] The invention relates to a tether drag de-orbit method, in particular to a tether drag derotation and de-orbit method for a failed liquid-filled spacecraft, which is suitable for the removal process of large space debris with residual liquid, and belongs to the technical field of aerospace. Background technique [0002] In recent decades, with the continuous exploration of space by human beings, near-Earth space technology has brought great convenience to people in communication, navigation, weather forecasting, deep space exploration, etc., and the earth orbit resources are increasingly valued by countries. However, human space activities are threatened by space debris, and its collision speed with spacecraft can reach 10km / s, which is extremely destructive. In-orbit spacecraft will be directly destroyed by larger space debris, while smaller space debris will also cause irreparable damage to the surface and even the interior of the spacecraft, shorten...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24G05D1/08
CPCB64G1/242G05D1/0825
Inventor 祁瑞姚傅祯姜泽华刘禹
Owner BEIJING INSTITUTE OF TECHNOLOGYGY