Simulation analysis of orbital parameters of small satellite launching by space tether system

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3 Scopus citations

Abstract

Two ways of launching small satellite to elliptical orbit and circular orbit are presented for the problems of using space tether system launching a small satellite. Through two mobile launching ways, the apogee height and perigee height of the small satellite are calculated both in elliptic orbit and approximate circular orbit. Then, Simulation analyzing the influence of the tether length, slip angle and the disturbance of in-plane angle on the apogee height and perigee height of the small satellite. The dynamics equations of the tether system are established in the orbital coordinate system, then, the initial velocity of small satellite is calculated. In order to establish the motion states of small satellite after cutting off the tether, the orbit equations of small satellite are established in the geocentric orbit coordinate system. After the simulation analysis, the optimal end points are obtained, which provide the theoretical basis for selection of end point of space tether system up deployed.

Original languageEnglish
Title of host publicationProceedings of the 33rd Chinese Control Conference, CCC 2014
EditorsShengyuan Xu, Qianchuan Zhao
PublisherIEEE Computer Society
Pages6398-6402
Number of pages5
ISBN (Electronic)9789881563842
DOIs
StatePublished - 11 Sep 2014
EventProceedings of the 33rd Chinese Control Conference, CCC 2014 - Nanjing, China
Duration: 28 Jul 201430 Jul 2014

Publication series

NameProceedings of the 33rd Chinese Control Conference, CCC 2014
ISSN (Print)1934-1768
ISSN (Electronic)2161-2927

Conference

ConferenceProceedings of the 33rd Chinese Control Conference, CCC 2014
Country/TerritoryChina
CityNanjing
Period28/07/1430/07/14

Keywords

  • Launching Small Satellite
  • Orbital Parameter
  • Slip Angle
  • Space Tether System

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