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TETHER STORAGE UNIT FOR ARTIFICIAL SATELLITES, AND ARTIFICIAL SATELLITE SYSTEM

Foreign code F210010483
File No. (S2020-0008-N0)
Posted date 2021年7月29日
Country 世界知的所有権機関(WIPO)
International application number 2020JP039272
International publication number WO 2021085217
Date of international filing 令和2年10月19日(2020.10.19)
Date of international publication 令和3年5月6日(2021.5.6)
Priority data
  • 特願2019-197135 (2019.10.30) JP
Title TETHER STORAGE UNIT FOR ARTIFICIAL SATELLITES, AND ARTIFICIAL SATELLITE SYSTEM
Abstract The present invention realizes efficient orbital transfer without complicating structure. A tether storage unit 5 for artificial satellites includes: a housing 11; a tether 13 which is stored in the housing 11 so as to be extendable outward from the housing 11; a moving object 23 which is stored in the housing 11 in a state of being attached to the tether 13 so as to be movable on the tether 13 extended from the housing 11 toward a tip of the tether 13; and a motor 25 for driving the tether 13 to extend and the moving object 23 to move on the tether 13.
Outline of related art and contending technology BACKGROUND ART
In recent years, the number of space debris (debris) (hereinafter, also simply referred to as "debris") has increased explosive to 20,000 or greater, and there is a need to suppress the occurrence of debris and remove debris. On the other hand, in recent years, the number of microsatellites has increased, and by using a large number of satellites, it is possible to realize high frequency overhead passage of the satellites on the Earth. Here, as long as the orbital control of the ultrasmall satellite is possible, the formation flight of a large number of satellites can be controlled, and the mission can be efficiently carried out.
The non-conductive tether or trajectory control technique using the conductive tether described in Non-Patent Document 1 described below and Patent Document 1 described below are known as techniques for realizing the removal of debris as described above. In this technology using electrically conductive tethers, orbital control of an artificial satellite system is performed by using Lorentz force acting on the tethers. Furthermore, the technology described in Patent Document 2 below is also known as a technology for attitude control using a tether.
  • Applicant
  • ※All designated countries except for US in the data before July 2012
  • SHIZUOKA UNIVERSITY
  • Inventor
  • NOUMI Masahiro
IPC(International Patent Classification)
Specified countries National States: AE AG AL AM AO AT AU AZ BA BB BG BH BN BR BW BY BZ CA CH CL CN CO CR CU CZ DE DJ DK DM DO DZ EC EE EG ES FI GB GD GE GH GM GT HN HR HU ID IL IN IR IS IT JO JP KE KG KH KN KP KR KW KZ LA LC LK LR LS LU LY MA MD ME MG MK MN MW MX MY MZ NA NG NI NO NZ OM PA PE PG PH PL PT QA RO RS RU RW SA SC SD SE SG SK SL ST SV SY TH TJ TM TN TR TT TZ UA UG US UZ VC VN WS ZA ZM ZW
ARIPO: BW GH GM KE LR LS MW MZ NA RW SD SL SZ TZ UG ZM ZW
EAPO: AM AZ BY KG KZ RU TJ TM
EPO: AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
OAPI: BF BJ CF CG CI CM GA GN GQ GW KM ML MR NE SN ST TD TG
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