1. WIRELESS POWER TRANSMISSION (WPT)
Microwave Beam
Laser Beam
Sunbeam
Redirected,
Reprocessed
Sunlight
Point of Contact: Richard M. Dickinson, Chairman NASA SSP Wireless Power Transmission Working Group
(818)
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2. 5.8 GHz, 500m Diameter, Retrodirective 2 GW Phased Array Antenna
by Richard M. Dickinson, JPL
2.5 GW DC/AC
mm
(~2 in.)
D= 9673
500 m
37,500 km
1.2 GWe
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3. 5.8 GHz Magnetron Directional Amplifier (MDA) SSP Subarrays*
by Richard M. Dickinson, JPL
Total “Average” Mass Density ~ 32 kg/m2
5 kW RF out, 85.5% efficient Magnetron, ~1kg,
6 kV, 1A & 70 W, 5s-Starting Filament & Off
44 cm dia., 350 deg C Pyrolytic
Graphite Radiator Dumping 850W
Waveguide Phase-Reference,
Circulator, Filters, ASIC-
MMIC, Buck-Boost Coil, Guide-
Tuner and Power Distribution
Peak Mass Density = 5.7 kg/m2
6 kg/m2
Absorptive & Reflective 2 kg/m2
HVDC Distribution kg/m2
TOTAL Peak Density = 14 kg/m2
Edge Subarray Density = 7.7 kg/m2
Two Central Devices Diplexed
for Retrodirective Pilot Beam
Receiver Function
MLI Blankets
Over 95 deg C
Electronics
Est. ~20kg/m2
Portion of 4m X 4m
Central Subarray with
9 X 9 = 81-MDAs
Yielding ~ 25 kW/m2 PFD
for 1.2 GWe System
Slotted Waveguide
Transmitting Antenna
~ 6 kg/m2, 0.5 mm (.02’)
Aluminum (~ 1100slots/m2)
~ 3.2 cm thick (Cross Feeds
+ Radiating Waveguides)
NOTE:
Not To Scale
4m X 4m
Edge Subarray
3 X 3 = 9-MDAs
Yielding ~ 2.8 kW/m2 PFD
and thus -9.5 dB Aperture Taper
* Var. of Brown, W. C.,”Satellite Power System (SPS) Magnetron Tube Assessment Study, “ NASA Contract NAS , for MSFC, 7/10/80.
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4. Slotted Waveguide Subarray Low Cost Manufacture
Concept by Bill Brown[1]
Punch
Registration
Cut Tab
Relief
Bend
Tab
Form Inter-
W/G Wall
Heavy Reynolds Wrap or Equiv.
Aluminum Sheet Stock
Punch
Registration
Punch Radiating
Waveguide Slots
Form
End Walls
Integrate Halves &
Spot Weld Assy.
Add Feed Guide to Assy.
with Magnetron Flange
8-Slot X 8-Stick
W/G Subarray
(front view)
W/G TOOLING NEEDS
TO BE DEVELOPED!
(back view)
1. Brown, W. C.,”Microwave Beamed Power Technology Development,” Final Report JPL Contract No , Raytheon PT-5613, May 15, 1980.
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5. Modified Microwave Oven Magnetrons for Space Solar Power Array Transmitter
Samsung Electronics takes great pride in the magnetron.
In 1978, the company succeeded in designing a filterless magnetron (model 2M184) which was the first design from which today's magnetrons are developed.
Today, 8 million magnetrons are produced on a fully automated manufact-
uring line and Samsung Electronics continues to develop new magnetrons
(for example, 10 vane magnetron, low noise magnetron, short antenna
magnetron, and high power magnetron) to improve quality and achieve
cost reductions, so that we can serve our customers with the best quality
and price possible.
e.g. Daewoo 2M218H
GHz
0.743 kg.
5.8 GHz Phase-
Injection Locked,
Pyrolytic Graphite
Thermal Radiator
5 kW MDA.
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6. Magnetron DC to RF Conversion Effficiency
Courtesy Douglas Parent of Commumications & Power Industries (CPI)
via Jim Benford of Microwave Sciences
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7. Bill Brown’s* Magnetron Directional Amplifier
Using A Modified Cooker Tube
Modified Cooker Magnetron
kV ~ 300mA
Buck-Boost Coil
H, 8.6 Ohms
Waveguide
Reactance
Tuner
Ferrite
Circulator
Amplitude
Comparator-
Driver
To Antenna
~ 2-3 W W
-50 dB
~ 30 dB Gain
Directional
Couplers
~ 75% Efficient
React-
ance
Driver
Power Output Ref.
~ 1/3500 V/W
~10 mW
Phaser Commands
Phaser Driver
Phase Comparator
~ 1 W
5- Bit
Phase
Shifter
2.45 GHz Ref. Signal
-20dB
RF Driver
Amplifier
Notes: By not powering the
magnetron, the low power
level RF driver signal can
be reflected through the
circulator to the antenna,
yielding a two-level unit.
Filament turned off after
start for clean spectrum**.
Supply Voltage
ASIC/MMIC
Needs Developing
Power Converter
WCB MDA MMIC-ASIC (TBD)
* Brown, William C.,”Development of Electronically Steerable Phased Array Module (ESPAM) with Magnetron Directional Amplifier (MDA) Power Source,”
Final Report, Microwave Power Transmission Systems, Weston MA, Texas A&M Research Foundation Subgrant No. L300060, Project RF , Sept
** McDowell, Hunter L.,”Magnetron Simulation Using a Moving Wavelength Computer Code,”IEEE Trans. Plasma Science, Vol. 26, No. 3, pp , June 1998.
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8. ISM Band Rainfall Impairment to SSP Microwave Beams-I
by Richard M. Dickinson, JPL 30 25 20 15 10 5
Location: Washington, DC-Clarksburg, MD Area, for ~47 deg Elevation
Ref. Reference Data for Engineers, 7th Ed.Sect. 27, SAMS 1985.
and Weather Statistics Almanacs. x
100 mm/hr
(~ 10 min duration/occurrence,
~once/yr but in 30 year return
period ~ 40 min duration)
(25”/hr=63.5mm/hr ~ 30 min
duration, ~ 2 times/yr)
Beam Power Loss at 47 deg. Elev., %
(Exceeded Rain Rate & Period: 60 mm/hr ~ 1 hr/yr) x
50 mm/hr
( Exceeded Rain Rate & Period: 30mm/hr ~ 10 hr/yr)
25 mm/hr x
10 mm/hr
(Exceeded Rain Rate & Period: ~1 week/yr, but in 30 yr return period ~ 18 hrs duration) x
5.8 GHz
5 mm/hr
2.45 GHz x x x
Cumulative Time, hrs/yr
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9. 100 80 60 40 20 ISM Band Rainfall Impairment to SSP Microwave Beams-II
ISM Band Rainfall Impairment to SSP Microwave Beams-II
by Richard M. Dickinson, JPL x x x x x
( 35 GHz*
Non ISM-Band) x x
Beam Power Loss at 47 deg. Elev., %
GHz**
Location: Washington, DC-Clarksburg, MD Area.
Ref. Reference Data for Engineers, 7th Ed.Sect. 27, SAMS 1985.
* Does not include ~ dB H20 & O2 Lines Absorption (-5.6%)
** Does not include ~ -1 dB H20-Line Absorption. ( -20.5%) x x x
5.8 GHz x x
2.45 GHz x x x
Cumulative Time, hrs/yr
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10. SSP Power Flux Density (PFD) Levels by Richard M. Dickinson, JPL
D = 500m,  = m (5.8GHz)
2 GW RF, ~10 dB Gauss Taper
GEO Altitude ~ 35,700 km
(Slant Range ~ 37,500 km)
~0.2 D2/km
Tubular-Beam Region }
“Far Field” Begins
at 2D2/ = 9,673 km
Peak Aperture PFD ~ 25 kW/m
(Ave PFD ~ 10 kW/m2)
Maximum PFD ~ 41 kW/m2
at ~ 34,733 km altitude
GPS Altitude = 20,200km
~400 V/m vs MIL-STD-461
Design Level of 200 V/m
Peak PFD ~ 440 W/m2
Peak PFD ~ 92 W/m2
Peak PFD ~ 90 W/m2
(Ave PFD ~ 37 W/m2)
~ 186 V/m vs NASA ISS
Test Level of 60 V/m
(S/C Time Thru Beam ~ 1 s)
~LEO Altitude = 350 km
Edge PFD ~ 0.9 mW/cm2
8000 m Dia.
Rectenna
~1.2 GW out
to ac grid
Tau=1.62, Beam Coupling Efficiency = 92.76%
Edge Taper = dB
Notes: Not To Scale &
Values Rounded.
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11. SSP Electromagnetic Power Flux Density & Related Phenomena
by Richard M. Dickinson, JPL 8 7 6 5 4 3 2 1
5.8 GHz
GEO
Log Altitude, m
LEO
7km/s flythrough of 7 km dia beam of 10 mW/cm2 = 10e-2 J/cm2
( Disruptive fluence** to cause bit errors in unshielded computers ~ 10e-7 J/cm2)
70K’
Sunlight
High Noon
Clear Day
~ 25,000 W/m2
(1.2 GWe Output
at Rectenna from
500m Transmitter)
SSP X
Visible Wavelengths
Russian Long Term Public Exposure*
Log Frequency, Hz
Ambient
Atmosphere
CW Breakdown** X
Polish Long Term Public Exposure & Russian 8 hr Occupational Exposure
Polish Continuous Occupational Exposure
Canadian General Public Exposure X
Canadian Occupational Exposure & US Oven at 5 cm Range
Western Europe Exposure Limit & Finch No Observable Response
Finch Moderate Response
Finch Intense Response
Potential Cataracts
Arcing in Protective Suits****
Log Power Flux Density, mW/cm2
~ Unshielded Electronic Equipment Device Destruction***
* Lindsay, I. R.,”Microwave Radiation: Biological Effects and Exposure Standards,” Space Solar Power Review, Vol. 2, pp , 1981.
** Benford, J. and Swegle, J., High Power Microwaves, pp. 18 & pp. 119, (Adapted from Reilly), Artech House, 1992.
*** Wunsch, D. and Bell, R.,”Determination of Threshold Failure Levels of Semiconductor Diodes and Transistors Due to Pulse Voltages,” IEEE
Trans. Nuclear Science, Vol. NS-15, pp , Dec
****Guy, A. et. al.,”Measurement of Shielding Effectiveness of Microwave-Protective Suits,” IEEE Trans. MTT-35, No. 11, p.984-, Nov
STP Air Breakdown
POL Ignition
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12. SSP Wireless Power Transmission Technology-I
by Richard M. Dickinson, JPL
Solid State Magnetron Klystron
Phase Injection Locked
1. SOA DC-RF Conversion -%/W/GHz/C .76/6.9/8.0/ /900/2.45/ /50kW/2.1/100
SSP Required= .90/6-60/5.8/ /5kW/5.8/ /26kW/5.8/500
2. SOA Large Phased Arrays (non Retrodirective) PAVE Cobra
THAAD ~2mX5m, 25,344 X-Band Elements m dia(twin)-3/4MW m dia-1MW(TWTs)
TRW- Capistrano HPM 48-6ft S-Band Dishes ,792 active elements of ,3600 elements
500m dia, ~2 GW CW out, #elements= 83,841, , ,589
EMC & 2ndHarmonic= & -40dBc & -60dBc & -30dBc
SSP EMC 5.8 GHz+/- 75 MHz & Fleet of ~ 100 SSP in View= -174dBW/m2/Hz?
4. SOA Spacecraft Filter Multipacting Breakdown Margin= 6-10dB at C & Ku-Band 10-50W, 13 yrs.
5.8GHz Margin Requirement >6 dB for 40 years= 60W kW 26kW
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13. SSP Wireless Power Transmission Technology-II
by Richard M. Dickinson, JPL
50-100V
3.5-6kV
28kV
Solid State Magnetron Klystron
Phase Injection Locked
5. SOA CW Microwave Power $/W, GHz, Quan.= $3, 1.9,100s $.025,2.45,100Ks $1.25,UHF,2s
SSP Required CW Microwave Power at 5.8 GHz, Fleet of 100 Quantity = $1-2/W,
6. SOA Microwave Device, Thermal & PMAD kW/kg=
SSP WPT Array System Specific Power (kW/kg)
Key Technology Item s PLL-ASIC 5-Stage
The near term technology to be developed is the ASIC/MMIC for using modified
cooker tube magnetrons as phased array sources for retrodirective power transmitting
phased arrays in beaming power to station keep geostationary stratospheric platforms
for telecommunication and scientific observation applications.
ASIC=Applicaion Specific Integrated Circuit GaN=Gallium Nitride MDC=Multiple Depressed Collector PLL=Phase Locked Loop
PMAD=Power Management & Distribution dBc=Decibels Below the Carrier Level dBW=Decibels Relative to a Watt
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14. SSP Wireless Power Transmission Technology-III
by Richard M. Dickinson, JPL
Barriers to SSP:
1. Electromagnetic Compatibility (EMC)-
A. Power Beam Frequency Allocation at wavelengths with less than 5% (0.2 dB)
atmosphere propagation impairment for 99.5% of a year. Bandwidth at auction
for less than $100/Hz? WPT Service definition in the International Telecommunicaton
Union by over 50% of the 182 member countries.
B. Close-In Carrier Noise and Harmonic Filtering in GEO, with less than 10%
(0.5 dB) insertion loss and greater than a safety factor of 2 (Voltage ratio,
6 dB Power) multipacting breakdown margin for less than 2 kg/m2 areal density.
Less than 15% (0.7 dB) insertion loss for ground based rectennas at less than $0.2/W.
2. Lifetime- 40 year lifetime for high power microwave devices and parts in GEO.
3. Beam Safety Perception- The “fear of frying” must be overcome by working demos
and public education of beam safety marking and intrusion detection with safe beam
interruption and restoration, for less than $.005/kWh delivered energy.
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15. WIRELESS POWER TRANSMISSION?
by Richard M. Dickinson, JPL
I. In order to obtain a service definition and frequency allocation for SSP use, it will be
necessary to show the ITU & FCC that the SSP can be designed and maintained
Electromagnetically Compatible with other users of the Radio Spectrum.
II. Because of the GW power levels and the rain of electromagnetic energy falling to Earth
from a fleet of SSP spacecraft functioning under various operational and environmental
conditions, it is required to filter the carrier noise outside the ISM band, to filter the
harmonics, to provide notch filters on the spacecraft and possibly on ground radio and
radar equipment functioning at certain sensitive frequencies outside the ISM bands.
III. There still exist large uncertainties in the WPT performance and the cost impacts due to
the lack of analysis, measurements, models and victim susceptibility data for determining
the SSP Electromagnetic Compatibility (EMC) requirements.
IV. Furthermore, a functioning WPT facility does not now exist to validate the adequacy
of mitigation approaches or the costs both economically and in filters insertion loss required
to achieve EMC both on the transmitters and on the rectennas.
V. Will careful engineering design be economically affordable and adequate to prevent
serious interference to other users of the electromagnetic Spectrum?
A WPT test facility is needed for verification tests & demos.
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16. SSP WPT Spatial & Spectral Interfaces
Amplitude of Power Density, W/m2
or Spectral Density, W/m2/Hz
ANSI/IEEE C95.1:
Human Exposure
@5.8 GHz in an
Uncontrolled Environment
< 3.87mW/cm2 Averaged
over 30 minutes.
Controlled Environment
<10mW/cm2 Averaged
over 6 minutes.
Dawn Trout IOM to Jeff Anderson
MSFC 8/31/98:
MIL-STD-461D EMC Tests:
A/C External V/m
Ship(Above Deck) V/m
Space V/m
MIL-STD-464 Design Levels:
General Systems V/m
Shipboard & Ordnance V/m
Ground Systems V/m
Space & Launch Veh V/m
NASA EMI Test Levels:
Space Station V/m
Shuttle & Shuttle P/L V/m
GSFC Satellites V/m
SAE J-1338
Automobiles V/m
Main
Beam
Space
(Sidelobes)
1st Grating Lobe
Fundamental
Sidelobe Envelope
Rectenna
Close-In
Carrier Noise
Power Supply
Ripple Modulation
...
2nd Harmonic
Sidelobe Envelope
3rd Harmonic
Sidelobe Envelope
GHz=Maritime
Radionavigation,
Meteorological Aids,
TDWR in ATC
...
Harmonic Envelope
Rectenna Site
Fence Boundary?
Fundamental nd rd th th th th th th th Harmonics
2X5.8=11.6
( =RA
R’cve Only,
=Fixed,
Fixed S/C Space-
Earth)
...
Note: Not to Scale
1st Sidelobe
3X5.8=17.4
( =
Fixed S/C
Earth-Space)
4X5.8=23.2
( =
Fixed, ISL,
Mobile)
NASA Spectrum Manager,
via Vern Heinen LeRC:
ITU-R SA-1157:
-250dBW/m2/Hz
ITU-R RA-769:
-240dBW/m2/Hz > 1 GHz
(Undisturbed Sun = -180dBW/Hz)
(World Countries= 239)
5X5.8=29
( =
Fixed, Fixed
S/C E-S,Mobile,
LMDS)
Frequency
(Spectrum
Sidebands)
5.8 GHz ISM= GHz
( =Radiolocation,
Amateur, ISM, Door Openers,
S.S.-Part 15 Devices, etc.)
Earth in the Band
GHz <
-138 to -148 dBW/m2/4 kHz
depending on arrival angle
(pp. 275 Kobb Guide)
...
...
Earth in the Band
GHz <
-101 dBW/m2/ 200 MHz
for all Angles ( pp. 268)
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17. B E A M E R RADAR SCIENCE ATMOSPHERE SCIENCE SYSTEM MODELING
Big Electromagnetic Array Microwave Energy Research Facility
An Integrated Space Solar Power Test & Demonstration Facility
by Richard M. Dickinson, JPL
RADAR SCIENCE
ATMOSPHERE
SCIENCE
SYSTEM MODELING
PERFORMANCE & $
RECTENNAS
for Commercial Platforms
SHADOW
EFFECTS
ANTENNA
PATTERNS &A/C
ACTIVE -TRUSS
BEAM TURNER
ROBOT
Phase Cal & Maintenance PV
by DOE?
PMAD
Interfaces,
Instrumentation &
Transients
RF ARRAY
BEAM SAFETY RADARS
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18. An International WPT Development and Test Facility for Beaming Power to Airships
by Richard M. Dickinson, JPL
OBJECTIVES:
1. Demonstrate a safe, electromagnetically compatible RF power beaming application
with commercial potential and NASA aeronautics and future space uses.
2. Enlist and involve international partners to promote ITU cooperation for SSP
frequency authorization and WPT service definition.
3. Begin a stage one system review with the NTIA for WPT beam power frequency.
4. Determine EMC filtering requirements for in-band noise, harmonics and IMP reductions.
4. Measure both rectenna and transmitting phased array patterns under operating conditions.
5. Develop WPT beam safety systems and techniques for aircraft, avian biota and spacecraft.
6. Encourage commercial WPT applications to reduce NASA infrastructure costs in the future.
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19. An International WPT Development and Test Facility for Beaming Power to Airships
by Richard M. Dickinson, JPL
BENEFITS:
1. Initiating the commercial beamed power roadmap for developing SSP & interstellar infrastructure.
2. Requesting the required NTIA certification of an available frequency for the power beam.
3. Demonstrating and building public confidence in safe beamed power operations.
4. Performing an end-to-end WPT system detail design and collecting real cost and performance data.
5. Conducting a WPT System Environmental Impact Study and devising mitigations.
6. Collecting reliability and availability data resulting from continued operations.
7. Reducing the uncertainty in the magnitude of insertion loss for the required EMC filters.
8. Beginning the real international cooperation that will be required for microwave SSP Systems.
9. Starting to work SSP concerns of the FAA, FDA, EPA, FCC, OSHA and state & local permit agencies.
10. Giving NASA a 21 km altitude geostationary research platform with lots of electric power capability.
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20. B E A M E R
An Integrated Space Solar Power Test & WPT Demonstration Facility
by Richard M. Dickinson, JPL
BEAMER
BEAMER
991205rmd
Big Electromagnetic Array Microwave Energy Research Facility

21. Mars Outpost Technology for Wireless Power Transmission Proposed Dust Buster Concept Study
by Richard M. Dickinson, JPL
Power-Efficiency Chain Design Control Table:
1. DC-80kV Conversion
2. Typ. 200kW , 245 GHz Gyrotron
3. 20m Array Element, /30 Surface Acc
4. 20 deg. rms Phase Accuracy
5. Aperture/Feed Efficiency
6. Circle Pack Fill Factor G/L Losses
7. Beam Coupling Efficiency..(-4dBtaper)
8. Dust Attenuation for Optical Depth of 6,
10km Scale Height, mean 20 micron dia.
Particle & Dielectric Constant 2-j0.4,
at 245 GHz....[1] to dB
9. Rectenna Collection-Conversion Eff
10. Output Power Conversion Efficiency
Overall DC in-DC-out Efficiency
(e.g. for 100kW out, 2.8MW input from PV PMAD)
Mars Terrain Outpost 150 m Rectenna
and Coring Rover Beamer Facility
245 GHz 17,000 km Aerosynch Orbit SSP
180 m Dia. Beamer (61ea 20 m Dia Inflatables)
[1] Smith, E. & Flock, W.,”Propagation Through Martian Dust at 8.5 and 32 GHz,” TDA Progress Report 42-87, pp , July-Sept
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22. Space Solar Power Technology Investment Plan Wireless Power Transmission
Richard M. Dickinson, JPL
DESCRIPTION
Microwave Beam Powered High-Altitude Platform(s), Radar Science, Telecommunications, Observation & in situ Atmosphere Science
APPROACH
In Partnership with Industry, Develop & Demonstrate a 2.45 GHz Pilot-Beam Steered Retrodirective Phased Array in the MW category of Commercial Significance
POTENTIAL PARTICIPANTS
NASA, DOD, EPA, TCOM, ILC Dover, Skystation Int’l, WP&L, DOE, Platforms Int’l, Lucent, Boeing, Raytheon, ESA, MITI?
Pilot
Signal
Safety
Radars
Control
Facility
Retrodirective
Phased Array
TECHNOLOGY ELEMENTS
Wireless Power Transmission Link Efficiency & Low Grating Lobes
Beam Power Safety Subsystem Reliability & Robotic Phase Calib.
Microwave Power Retrodirective Array Pointing Accuracy
Demonstration of Electromagnetic Compatibility, X’mit & R’cve
High-Altitude, High-Power Platforms for Telecom & Observation
Demonstrate Simultaneous Multiple Beam Power Beaming
MAJOR MILESTONES
Secure Commercial Partners and Obtain FCC/NTIA Experimental
Frequency License, Involve Public in Safety System Development
Perform Detail Design & Fix Development Schedule
Fab & Test Transmitting Array, Rectenna & Airship/Aircraft
Integrate Rectenna, Science Payload and Launch Airship/Aircraft
Operate System & Collect Sci. & Test Data, Evaluate Feasibility
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