Success rate and effect of using electrodynamic tether system for de-orbit leo spacecraft

Ieyoung Kim, Toshiya Hanada, Hiroshi Hirayama

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The near-Earth orbit debris population will continue to increase due to ongoing space activities, on-orbit explosions, and accidental collisions among artificial objects in space. To better limit the growth of debris population, Active Debris Removals have been proposed as effective and potential mitigation methods. In Japan, an active debris removal using electro-dynamic tether to reduce large space debris in the low-earth orbit is considered. However, tether satellite system must solve two matters in order to execute the mission successfully. First, a tether strands is thin but long enough to have a large area so that it is vulnerable to small particles. This paper suggests a double tether system and provides a mathematical approach to estimate the survival probability of a double tether system and then apply the approach to evaluate the mission success rate. Second, the tether is also long enough to be a hazard to other operational spacecraft. This paper also provides a simulation of tether satellite's impact probability to the other spacecraft and aims to propose the measurement for mission success.

Original languageEnglish
Title of host publication60th International Astronautical Congress 2009, IAC 2009
Pages1870-1879
Number of pages10
Publication statusPublished - Dec 1 2009
Event60th International Astronautical Congress 2009, IAC 2009 - Daejeon, Korea, Republic of
Duration: Oct 12 2009Oct 16 2009

Publication series

Name60th International Astronautical Congress 2009, IAC 2009
Volume3

Other

Other60th International Astronautical Congress 2009, IAC 2009
CountryKorea, Republic of
CityDaejeon
Period10/12/0910/16/09

Fingerprint

spacecraft orbits
electrodynamics
debris
spacecraft
space debris
explosion
mitigation
collision
hazard
Earth orbits
low Earth orbits
strands
hazards
simulation
explosions
Japan
orbits
collisions
effect
removal

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Astronomy and Astrophysics

Cite this

Kim, I., Hanada, T., & Hirayama, H. (2009). Success rate and effect of using electrodynamic tether system for de-orbit leo spacecraft. In 60th International Astronautical Congress 2009, IAC 2009 (pp. 1870-1879). (60th International Astronautical Congress 2009, IAC 2009; Vol. 3).

Success rate and effect of using electrodynamic tether system for de-orbit leo spacecraft. / Kim, Ieyoung; Hanada, Toshiya; Hirayama, Hiroshi.

60th International Astronautical Congress 2009, IAC 2009. 2009. p. 1870-1879 (60th International Astronautical Congress 2009, IAC 2009; Vol. 3).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Kim, I, Hanada, T & Hirayama, H 2009, Success rate and effect of using electrodynamic tether system for de-orbit leo spacecraft. in 60th International Astronautical Congress 2009, IAC 2009. 60th International Astronautical Congress 2009, IAC 2009, vol. 3, pp. 1870-1879, 60th International Astronautical Congress 2009, IAC 2009, Daejeon, Korea, Republic of, 10/12/09.
Kim I, Hanada T, Hirayama H. Success rate and effect of using electrodynamic tether system for de-orbit leo spacecraft. In 60th International Astronautical Congress 2009, IAC 2009. 2009. p. 1870-1879. (60th International Astronautical Congress 2009, IAC 2009).
Kim, Ieyoung ; Hanada, Toshiya ; Hirayama, Hiroshi. / Success rate and effect of using electrodynamic tether system for de-orbit leo spacecraft. 60th International Astronautical Congress 2009, IAC 2009. 2009. pp. 1870-1879 (60th International Astronautical Congress 2009, IAC 2009).
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