1 / 6

CO2 Emission from Solar Power satellite (SPS) Multi-Tether Satellite System

CO2 Emission from Solar Power satellite (SPS) Multi-Tether Satellite System. Keiichiro Asakura Faculty of Economics , Ryutsu Keizai University 120 , Ryugasaki City, Ibaraki 301-8555, Japan E-mail:asakura@rku.ac.jp Satoshi Nakano Keio Economic Observatory (KEO) , Keio University

gisela-chapman
Download Presentation

CO2 Emission from Solar Power satellite (SPS) Multi-Tether Satellite System

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. CO2Emissionfrom Solar Power satellite (SPS) Multi-Tether Satellite System Keiichiro Asakura Faculty of Economics , Ryutsu Keizai University 120 , Ryugasaki City, Ibaraki 301-8555, Japan E-mail:asakura@rku.ac.jp Satoshi Nakano Keio Economic Observatory (KEO) , Keio University 2-15-45 Mita, Minatoku, Tokyo 108-8345, Japan Kanji Yoshioka Keio Economic Observatory (KEO) , Keio University 2-15-45 Mita, Minatoku, Tokyo 108-8345, Japan Multi-Tether Satellite system is developed by Professor Susumu SASAKI, Japan Aerospace Exploration Agency: JAXA .We would like to thank him for giving us technical information and helpful comments. We are solely responsible for any errors.

  2. Satellite Geo-Stationary Orbit 36,000km Tether Photo-voltaic panel 2.5km ×2.5km Upper panel:2.8GW Lower panel:2.5GW Concept of SPS Orbital Transfer Vehicle（OTV） Payload;50ｔ Propellant；LAｒ,30t 1unit;145t Total：171unit,600 round trips Microwave Low Earth Orbit Reusable Launch Vehicle （RLV） Payload ：50ｔ Propellant；LH2,250t LO2,1,500t 1unit;2,000t Total:14unit,1000 round trips Electric power 1GW RectennaDiameter;3.5km Earth’s Surface

  3. Model and Data 1.Model - Environmental I-O Analysis CO2k= C (I-A)-1 fk・・・（1） C：CO2 emission coefficient (diagonal) (I-A)-1：Leontief Inverse Matrix f k: final demand vector of k-th SPS components (e.g. Satellite,Orbital Transfer Vehicle,Rectenna・・・) CO2k :CO2 emission of k-th SPS component 2.Data (a) Japanese Environmental I-O Table (b)SPS Material data

  4. MakingSPSFinalDemand Main data source of FD vectors estimated are; DOE/NASA(1980),Society of Chemical Engineers(1995) Yearbook Machinery Statistics, Unit price information in IO Databases Naruo(1996) andSasaki(2006)

  5. Overview of the CO2 Emissionfrom SPS CO2 Emission by main components OTV; Orbital Transfer Vehicle RLV; Reusable Launch Vehicle PV; photovoltaics cell LAr; Liquid argon LH2; Liquid hydrogen LO2; Liquid oxygen CO2 Emission by sector

  6. Comparison of CO2 emission of different electricity generation systems g-CO2/kWh *Figures on Coal,Oil,LNG,Nuclear and PV1 are estimated by Hondo(2000). Figure on PV2 is recalculation on Nakano(2006),using eq.(1).Figures on several types of SPS are estimated by our group. *Life time assumption on Multi-Tether Satellite system; 40 years. *Total repair ratio of Multi-Tether Satellite system is assumed to be 2.5%,CO2 emission /kWh becomes 33g, if it is permitted to assume it simply. *CO2 emission in distributing the electricity generated is not included in the SPS figures (since the data is not available) but is included for the other systems. →several types of SPS

More Related