2013 Update to Space-Based Solar Power
by Mr. Hubert P. Davis, Mr. Richard Dickinson, Dr. Ted Talay,
Mr. Gordon Woodcock, Members, SolarHigh Study Group
to the AIAA SOSTC Workshop at Southwest Research Institute, San Antonio, Texas May 1, 2013
NASA/DoE Boeing 1979 Reference System Illustrated, 2013 not yet ready
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Note: This presentation is a technical description of our teams’ 2013 results. Mr. Gordon Woodcock
will later summarize our cost analysis methodology and its’ results.
Summary
• The SolarHigh Study Group is a a small group of volunteers
formed in mid-2011 for a single purpose:
 Update the 1979, well-documented, study by the Boeing
Company of Dr. Peter Glaser’s Space-Based-Solar-Power
System Concept (SBSP)
 To provide baseload electrical power to many Earth-based
electrical power networks using sunlight as the energy
source
• This early work was done under contract to NASA-Johnson
Space Center & DoE for ~ $10millions+
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Findings of late 1979 were:
1. Baseload (Dispatchable) Power from Space is technically
feasible using 1979 technologies
2. Safe for mankind and all other living things
3. Environmentally favorable to a remarkable extent,
including greatly reduced use of water & land, very little
fuel - - for transportation, not used for power production.
4. Predicted (using standard utility industry Levelized Cost of
Energy [LCOE] methodology) to produce electricity for 2 to 3
cents/kWh more than that produced by burning coal.
• The DoE Secretary cancelled the program in January
1980.
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Objectives for 2013
• Use three decades of relevant technology
advancements to lower mass and cost
• Employ limited system advancements to
improve upon the 1979 concept:
• To the best of our limited resources:
• Redefine the 1979 results
• Generate Preliminary Costs and LCOE
(To be provided later by Mr. Gordon Woodcock)
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SolarHigh 2013 Participants
• Hubert P. Davis - - former USAF (Korea) and NASA Johnson
Space Center (JSC), Manager of LM-5 Eagle, (first to land on the
moon). As Manager of JSC Future Programs Office, persuaded
NASA to study SBSP, A leader of the1970’s study
• Gordon Woodcock - - Boeing Company retiree, associated with
Saturn V design and construction, Study Manager for many NASA
studies of future space initiatives, chief designer of Boeing SBSP
Reference System Study of the 1970’s.
• Dr. Richard Dickinson - -Jet Propulsion Laboratory retiree, ran
1970’s study of microwave power transmission, including test
demonstration of feasibility, managed similar work in 1970’s study
• Dr. Ted Talay – NASA Langley Research Center retiree,
managed LaRC Vehicle Analysis Branch, including multi-year study
of replacement vehicles for the Space Shuttle and for Heavy Lift.
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Attributions
• Mr. Sam Turcotte Davis, Mr. Rolando Espinosa and
Mr. at Zukor International of San Antonio, Texas
provided the art work for this presentation as a fellow
volunteer. Their support is greatly appreciated.
• Many other friends provided data, useful suggestions
and critiques. Their help added to our output and we
thank them.
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Major Changes from 1979 Boeing/NASA/DoE
SBSP Reference System
• Employ 2013 technologies rather than those of 1979
• Eliminate major Geo-Stationary Orbit 500-person
manufacturing base by using large Earth-manufactured
elements assembled and then extended in space by robots.
• Reduce output of each system from 5 Gwe to 2 Gwe to
better match terrestrial network capacities and reduce first
costs.
• Alter microwave transmission downlink frequency from 2.45
GHz to 5.8 GHz to reduce transmitter size from 1-km
diameter to 500 m, reducing mass and cost with acceptable
loss in transmission efficiency.
• Improve design of transmitter for commonality of elements
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and reduce I^2R losses
Precedent for Space-Based Solar Power:
Apollo 11 Lunar Landing of July 20, 1969
The United States “did the impossible” before - - we can do it again
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Why Go into Space for Solar Electricity?
Total Annual Sunlight, kWh/m2
17.6%
Much More Sunlight
Constant rather than Intermittent
Requires Very Little Energy Storage!
Solar9High
2012 Concept Solar Power Generation/Transmission
(
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2013 Concept Solar Power Generation/Transmission
(Show Earth-facing side with four antenna
elements on masts. Insert labels of parts and
dimensions)
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Fully Reusable Bimese Launcher Concept
Common Booster & Orbiter Elements
Updated from several years of work by NASA Langley
Research Center on Space Shuttle II
Payload bay = 6.5-m dia x 23-m length
Payload: 60 mt to assembly orbit
plus ~15 ton cylinder payload adapter
• Dry Mass Booster = 460 Klb, Dry Mass Orbiter = 559 Klb
• >70% of total liftoff mass is inexpensive liquid oxygen
propellant.
• Launch from equatorial sites to permit multiple launches/day.
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2013 SolarHigh Launch Concept
Payload Capability vs. Orbit Altitude
80
75
Payload, mt
70
0 deg inclination
Equatorial launch
65
60
55
28.5 deg inclination
KSC launch
50
51.6 deg inclination
KSC launch
45
40
100
125
150
175
200
225
250
275
Circular Orbit Altitude, nmi
Orbit Maneuvering System (OMS) system designed for
250 nmi circular orbit from initial 30 x 120 nmi injection
New, highly capable and low cost space transportation system enables many other
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useful space endeavors, military, civil space exploration and private sector
Launch & Deploy Element Operations
Solar Power Satellite Elements
Assembly Orbit: GSO + TBD km
Self-transfer completed SPS to
GSO using electric propulsion
Geosynchronous, or Geo-Stationary Orbit (GSO)
35,786 km (19,323 NM) altitude
Electric Orbital
Transfer Vehicles
(EOTV)
deliver SPS elements
to beyond GSO;
Returna to LEO orbit
EOTV
450 km (243 NM)
low-Earth orbit (LEO)
to LEO Propellant Depot
Bimese launch vehicle delivers up to 75 metric ton
SPS pre-built elements to LEO
EARTH
2013 SolarHigh System Concept
System Mass Properties
Metric Tons
Kg/kWe
Solar Array & Support Structure
Microwave Transmitter & Support
5,891
2.95
Power Management & Distribution
Attitude Control & Station-keeping
Avionics, Communications & Control
Other Systems & Propellants
Reserve Mass @ 10%
__________
Total in Space Mass, Metric Tons =
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(The Rectenna is on Earth)
2013 SolarHigh
Electrical Power Distribution & Losses
Solar Array Power Aver. Output, Initial
GWe
5.5
Solar Array Power Aver. Output, end of 30 year life
(assumes X% Loss due to radiation damage & other losses)
PM&D Power Losses (rejected to space)
Antennae Losses (rejected to space)
Rectenna Losses (rejected to biosphere)
Average Power Delivered to the Grid 24/7)
Efficiency, Power to Grid, (% of daily sunlight)
2.0
=%
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2013 SolarHigh Solar Array
Array Type
Initial Efficiency, %
Fill Factor, %
Initial Output Power Rating, Gwe
30 yr. End of Life Power Rating, Gwe
Array Size, km^2
Array Total Length, km
Array Width, incl. Center Body, km
Solar Array Total Mass, metric tons
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2013 SolarHigh Structures
Type - - multiple type composite structures
Total Length, Center Body, km
Center Body Diameter, meters
Center Body Source, Payload Canisters
Peripheral Structure Type – GrEp Deployed Truss
Peripheral Structure, Total Length, km
Interior Structure Type - GrEp Deployed Truss
Total Structural Mass, metric tons
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2013 SolarHigh
On-board Power Management & Distribution
Gordon
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2013 SolarHigh Microwave Transmitter
Drawn from Dick’s presentation, may take 2 or even 3
slides
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2013 SolarHigh System Rectenna
Drawn from Dick’s presentation, may take 2 slides
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Conclusions
2013 system is greatly improved over its 1979
predecessor
Preliminary cost analysis is expected to be much
lower (A later Woodcock Presentation)
Improved system costs may produce baseload
electrical power for Earth that competes well with
present energy options
Further study is warranted - - Now!!
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Recommendations
Review this work by a competent team, re-doing the 1979 systems
analysis at the level of detail done then. Include a large Powerplant A&E
firm & EPRI as well as aerospace firms. Assign this task to NASA-JSC.
Cost of this one year of work beginning in mid-2014 will be $50-100 mm,
but its benefits can be enormous.
In parallel, conduct critical tests, including some space tests in or near the
ISS to reduce program risks; about $100 mm.
If our results are confirmed or improved upon, begin implementation of
SBSP, with the United States leading an international effort to bring
benefits to all mankind.
Early efforts must include development and fielding of a new, fully reusable space transportation and space assembly infrastructure, essential
to SBSP & usable by many others.
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