Presentation	2000/6/23 SANE2000-23 Space Devris Mitigation Design Standard Akira Kato,
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Abstract(in Japanese)	(See Japanese page)
Abstract(in English)	As the space debris mitigation measures, prevention of on-orbit breakups of mission ended systems(venting propellants, cut-off charging lines of batteries, LBB design for pressure vessels, etc.), reorbit from GEO, and limiting the released parts(trapping the fragments from explosive bolts, etc.)have already been applied generally. However, the shielding or redundant design for the impacting small debris has not been taken, since the collision probability is not so large as the increase of mass is reasonable. In future development of infrastructure and technology are expected to conduct the collision avoidance maneuvers, and controlled reentry for the disposal of LEO systems.
Keyword(in Japanese)	(See Japanese page)
Keyword(in English)	space debris / on-orbit breakups / reorbit from GEO / space debris mitigation standard
Paper #	SANE2000-23
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Conference Information
Committee	SANE
Conference Date	2000/6/23(1days)
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Paper Information
Registration To	Space, Aeronautical and Navigational Electronics (SANE)
Language	JPN
Title (in Japanese)	(See Japanese page)
Sub Title (in Japanese)	(See Japanese page)
Title (in English)	SANE2000-23 Space Devris Mitigation Design Standard
Sub Title (in English)
Keyword(1)	space debris
Keyword(2)	on-orbit breakups
Keyword(3)	reorbit from GEO
Keyword(4)	space debris mitigation standard
1st Author's Name	Akira Kato
1st Author's Affiliation	National Space Development Agency of Japan()
Date	2000/6/23
Paper #	SANE2000-23
Volume (vol)	vol.100
Number (no)	162
Page	pp.pp.-
#Pages	6
Date of Issue