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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:[email protected]
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.
1
Concept of SPS
Satellite
Geo-Stationary Orbit
36,000km
Tether
Photo-voltaic panel
2.5km ×2.5km
Upper panel:2.8GW
Lower panel:2.5GW
Low Earth Orbit
Orbital Transfer Vehicle
（OTV）
Microwave
Payload;50ｔ
Propellant；LAｒ,30t
1unit;145t
Total：171unit,600 round trips
Reusable Launch Vehicle
（RLV）
Electric power
Rectenna
Diameter;3.5km
Earth’s
Surface
1GW
Payload ：50ｔ
Propellant；LH2,250t LO2,1,500t
1unit;2,000t
Total:14unit,1000 round trips
2
Model and Data
1.Model - Environmental I-O Analysis
CO2 k= 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・・・)
CO2 k :CO2 emission of k-th SPS component
2.Data
(a) Japanese Environmental I-O Table
(b)SPS Material data
3
Making SPS Final Demand
② IO sector　① Material Input information
(e.g. Satellite)
Resource
Requirements
Silicon Transistor
Silicon diode
ＭＰＵ
（CPU）
ＤＲＡＭ
・
・
・
material
input
Unit price
a
b
c
d
・
・
・
p_a
p_b
p_c
p_d
・
・
・
IO classification
prices
Semiconductor devices
Semiconductor devices
Integrated circuits
Integrated circuits
・
・
・
a×(p_a)
b×(p_b)
c×(p_c)
d×(p_d)
・
・
・
③ Add　Margin (FD)
IO classification
prices
Main data source of FD vectors estimated are;
Semiconductor devices
Semiconductor devices
Integrated circuits
Integrated circuits
a×(p_a)
b×(p_b)
c×(p_c)
d×(p_d)
・
・
trade and transport margin
・
・
・
m1
m2
・
DOE/NASA(1980),Society of Chemical Engineers(1995)
Yearbook Machinery Statistics,
Unit price information in IO Databases
Naruo(1996) and Sasaki(2006)
4
Overview of the CO2 Emission from SPS
CO2 Emission by main components
component
Satellite
Structure
PV
OTV
Structure
LAr
PV
RLV
Structure
LO2,LH2
Recttna
Total
thousand ton
1,116.9
2,659.7
74.6
61.0
184.6
46.6
6,406.9
693.4
11,243.7
share(%)
9.9%
23.7%
0.7%
0.5%
1.6%
0.4%
57.0%
6.2%
100.0%
CO2 Emission by sector
1
2
3
4
5
6
7
8
9
10
sector
Electricity
private power generation
road freight transport
coal products
pig iron
compressed gas, liquefied gas
coastal and inland watertransport
self-transport by private cars
sheet glass, safety glass
petroleum refinery products
others
Total
thousand ton
5,927.6
727.8
575.9
455.5
454.6
437.6
266.6
206.9
200.7
163.8
1,826.6
11,243.7
share(%)
52.7
6.5
5.1
4.1
4.0
3.9
2.4
1.8
1.8
1.5
16.2
100.0
OTV; Orbital Transfer Vehicle
RLV; Reusable Launch Vehicle
PV; photovoltaics cell
LAr; Liquid argon
LH2; Liquid hydrogen
LO2; Liquid oxygen
Comparison of CO2 emission of
different electricity generation systems
g-CO2/kWh
1200
1000
975
742
800
608
Operations
Construction
600
400
58
49
32
Multi-Tether
PV 2
11
USEF-baseline
PV 1
20
NEDO Grand Design
76
DOE/NASA:Breeder
53
DOE/NASA
22
Nuclear power
200
0
LNG
Oil
Coal
*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
6