WIRELESS POWER TRANSMISSION WPT Microwave Beam Laser Beam

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) 354 -2359. 000728 rmd

5. 8 GHz, 500 m Diameter, Retrodirective 2 GW Phased Array Antenna by Richard M. Dickinson, JPL 2. 5 GW DC/AC 500 m mm (~2 in. ) D = 9673 37, 500 km 1. 2 GWe 000605 rmd

5. 8 GHz Magnetron Directional Amplifier (MDA) SSP Subarrays* by Richard M. Dickinson, JPL Total “Average” Mass Density ~ 32 kg/m 2 Peak Mass Density = Transmitter@ 5. 7 kg/m 2 Antenna @ 6 kg/m 2 Absorptive & Reflective Filters @ 2 kg/m 2 HVDC Distribution Lines@0. 263 kg/m 2 TOTAL Peak Density = 14 kg/m 2 Edge Subarray Density = 7. 7 kg/m 2 Est. PMAD@1. 5 kg/k. W ~20 kg/m 2 5 k. W RF out, 85. 5% efficient Magnetron, ~1 kg, 6 k. V, 1 A & 70 W, 5 s-Starting Filament & Off 44 cm dia. , 350 deg C Pyrolytic Graphite Radiator Dumping 850 W MLI Blankets Over 95 deg C Electronics Waveguide Phase-Reference, Circulator, Filters, ASICMMIC, Buck-Boost Coil, Guide. Tuner and Power Distribution Portion of 4 m X 4 m Central Subarray with 9 X 9 = 81 -MDAs Yielding ~ 25 k. W/m 2 PFD for 1. 2 GWe System Slotted Waveguide Transmitting Antenna ~ 6 kg/m 2, 0. 5 mm (. 02’) Aluminum (~ 1100 slots/m 2) ~ 3. 2 cm thick (Cross Feeds + Radiating Waveguides) Two Central Devices Diplexed for Retrodirective Pilot Beam Receiver Function NOTE: Not To Scale 4 m X 4 m Edge Subarray 3 X 3 = 9 -MDAs Yielding ~ 2. 8 k. W/m 2 PFD and thus -9. 5 d. B Aperture Taper * Var. of Brown, W. C. , ”Satellite Power System (SPS) Magnetron Tube Assessment Study, “ NASA Contract NAS-8 -33157, for MSFC, 7/10/80. 991123 rmd

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 W/G TOOLING NEEDS TO BE DEVELOPED! (front view) (back view) 1. Brown, W. C. , ”Microwave Beamed Power Technology Development, ” Final Report JPL Contract No. 955104, Raytheon PT-5613, May 15, 1980. 991229 rmd

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 2 M 184) which was the first design from which today's magnetrons are developed. Today, 8 million magnetrons are produced on a fully automated manufacturing 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 2 M 218 H 600 W @ 2. 45 GHz 0. 743 kg. http: //samsungelectronics. com/products/microwaveoven/magnetron. html 5. 8 GHz Phase. Injection Locked, Pyrolytic Graphite Thermal Radiator 5 k. W MDA. 000605 rmd

Magnetron DC to RF Conversion Effficiency Courtesy Douglas Parent of Commumications & Power Industries (CPI) via Jim Benford of Microwave Sciences 991105 rmd

Bill Brown’s* Magnetron Directional Amplifier Using A Modified Cooker Tube Modified Cooker Magnetron 3. 35 -3. 85 k. V ~ 300 m. A Buck-Boost Coil 0. 0024 H, 8. 6 Ohms Amplitude Comparator. Driver Waveguide Ferrite Reactance Circulator Tuner ~ 2 -3 W 300 -1000 W -50 d. B ~ 30 d. B Gain Power Output Ref. To Antenna ~ 1/3500 V/W Phaser Commands 2. 45 GHz Ref. Signal Supply Voltage ASIC/MMIC Power Converter Needs Developing ~ 75% Efficient ~10 m. W Phaser Driver 5 - Bit Phase Shifter Reactance Driver Directional Couplers Phase Comparator ~1 W -20 d. B RF Driver Amplifier WCB MDA MMIC-ASIC (TBD) 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**. * 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. L 300060, Project RF-2500 -95, Sept. 1995. ** Mc. Dowell, Hunter L. , ”Magnetron Simulation Using a Moving Wavelength Computer Code, ”IEEE Trans. Plasma Science, Vol. 26, No. 3, pp. 733 -754, June 1998. 991102 rmd

ISM Band Rainfall Impairment to SSP Microwave Beams-I by Richard M. Dickinson, JPL Beam Power Loss at 47 deg. Elev. , % 30 Location: Washington, DC-Clarksburg, MD Area, for ~47 deg Elevation 25 x 100 mm/hr Reference Data for Engineers, 7 th Ed. Sect. 27, SAMS 1985. and Weather Statistics Almanacs. (~ 10 min duration/occurrence, ~once/yr but in 30 year return period ~ 40 min duration) 20 (25”/hr=63. 5 mm/hr ~ 30 min duration, ~ 2 times/yr) 15 (Exceeded Rain Rate & Period: 60 mm/hr ~ 1 hr/yr) x 10 50 mm/hr ( Exceeded Rain Rate & Period: 30 mm/hr ~ 10 hr/yr) x 25 mm/hr 5 0 10 mm/hr x x x 0 (Exceeded Rain Rate & Period: ~1 week/yr, but in 30 yr return period ~ 18 hrs duration) 5. 8 GHz 5 mm/hr 2. 45 GHz x 10 20 Cumulative Time, hrs/yr 30 40 990820 rmd

100 x x ISM Band Rainfall Impairment to SSP Microwave Beams-II by Richard M. Dickinson, JPL x Beam Power Loss at 47 deg. Elev. , % x 80 x ( 35 GHz* Non ISM-Band) 60 x x 24. 125 GHz** 40 Location: Washington, DC-Clarksburg, MD Area. x x Reference Data for Engineers, 7 th Ed. Sect. 27, SAMS 1985. 20 * Does not include ~ -0. 25 d. B H 20 & O 2 Lines Absorption (-5. 6%) x x 0 x 2. 45 GHz 20 5. 8 GHz ** Does not include ~ -1 d. B H 20 -Line Absorption. ( -20. 5%) x 40 Cumulative Time, hrs/yr 60 80 x 100 990823 rmd

SSP Power Flux Density (PFD) Levels by Richard M. Dickinson, JPL D = 500 m, = 0. 0517 m (5. 8 GHz) 2 GW RF, ~10 d. B Gauss Taper GEO Altitude ~ 35, 700 km ~0. 2 D 2/ km (Slant Range ~ 37, 500 km) Tubular-Beam Region “Far Field” Begins Peak Aperture PFD ~ 25 k. W/m at 2 D 2/ = 9, 673 km 2) } (Ave PFD ~ 10 k. W/m Maximum PFD ~ 41 k. W/m 2 at ~ 34, 733 km altitude Peak PFD ~ 440 W/m 2 GPS Altitude = 20, 200 km ~400 V/m vs MIL-STD-461 Design Level of 200 V/m ~LEO Altitude = 350 km ~ 186 V/m vs NASA ISS Test Level of 60 V/m Peak PFD ~ 92 W/m 2 Peak PFD ~ 90 W/m 2 (Ave PFD ~ 37 W/m 2) Edge PFD ~ 0. 9 m. W/cm 2 Notes: Not To Scale & Values Rounded. 8000 m Dia. Rectenna ~1. 2 GW out to ac grid (S/C Time Thru Beam ~ 1 s) Tau=1. 62, Beam Coupling Efficiency = 92. 76% Edge Taper = -10. 5 d. B 981214 rmd

SSP Electromagnetic Power Flux Density & Related Phenomena by Richard M. Dickinson, JPL 6 LEO 5 70 K’ 4 5. 8 GHz 7 km/s flythrough of 7 km dia beam of 10 m. W/cm 2 = 10 e-2 J/cm 2 ( Disruptive fluence** to cause bit errors in unshielded computers ~ 10 e-7 J/cm 2) 3 ~ 25, 000 W/m 2 (1. 2 GWe Output at Rectenna from 500 m Transmitter) Sunlight High Noon Clear Day 2 SSP 1 0 Russian Long Term Public Exposure* 8 9 10 11 12 13 Polish Long Term Public Exposure & Russian 8 hr Occupational Exposure -3 X 14 15 Log Frequency, Hz -1 -2 Ambient X Atmosphere CW Breakdown** Visible Wavelengths Log Altitude, m 8 GEO 7 5 1 2 4 ~ Unshielded Electronic Equipment Device Destruction*** 6 7 Lo g Po w er F lu x D 3 en sit y , m W /c m 2 0 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**** STP Air Breakdown POL Ignition * Lindsay, I. R. , ”Microwave Radiation: Biological Effects and Exposure Standards, ” Space Solar Power Review, Vol. 2, pp. 103 -108, 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. 244 -259, Dec. 1968. ****Guy, A. et. al. , ”Measurement of Shielding Effectiveness of Microwave-Protective Suits, ” IEEE Trans. MTT-35, No. 11, p. 984 -, Nov. 1987. 991119 rmd

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. 0/125 SSP Required=. 90/6 -60/5. 8/300 2. SOA Large Phased Arrays (non Retrodirective) THAAD ~2 m. X 5 m, 25, 344 X-Band Elements TRW- Capistrano HPM 48 -6 ft S-Band Dishes . 83/900/2. 45/135. 855/5 k. W/5. 8/350 . 83/26 k. W/5. 8/500 PAVE PAWS@UHF Cobra Dane@L-Band 31 m dia(twin)-3/4 MW 29 m dia-1 MW(TWTs) 1, 792 active elements of 5354 15, 3600 elements SSP @5. 8 GHz, 500 m dia, ~2 GW CW out, #elements= 83, 841, 253 3. 2. 45 EMC d. Bc/Hz@50 MHz & 2 nd. Harmonic= . 72/50 k. W/2. 1/100 -150 & -40 d. Bc 381, 618 82, 589 -190 & -60 d. Bc -160 & -30 d. Bc SSP EMC Requirement @ 5. 8 GHz+/- 75 MHz & Fleet of ~ 100 SSP in View= -174 d. BW/m 2/Hz? 4. SOA Spacecraft Filter Multipacting Breakdown Margin= 6 -10 d. B at C & Ku-Band 10 -50 W, 13 yrs. SSP @ 5. 8 GHz Margin Requirement >6 d. B for 40 years= 60 W 5 k. W 26 k. W 000320 rmd

SSP Wireless Power Transmission Technology-II by Richard M. Dickinson, JPL 50 -100 V Solid State 3. 5 -6 k. V 28 k. V Magnetron Klystron Phase Injection Locked 5. SOA CW Microwave Power $/W, GHz, Quan. = $3, 1. 9, 100 s $. 025, 2. 45, 100 Ks $1. 25, UHF, 2 s SSP Required CW Microwave Power at 5. 8 GHz, Fleet of 100 Quantity = $1 -2/W, 105 -109 6. SOA Microwave Device, Thermal & PMAD k. W/kg=. 01 SSP WPT Array System Specific Power (k. W/kg) Key Technology Item s . 42 . 02 . 34 . 3 Ga. N@300 C PLL-ASIC 5 -Stage MDC@500 C 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 Ga. N=Gallium Nitride MDC=Multiple Depressed Collector PLL=Phase Locked Loop PMAD=Power Management & Distribution d. Bc=Decibels Below the Carrier Level d. BW=Decibels Relative to a Watt 000322 rmd

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 d. B) 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 d. B) insertion loss and greater than a safety factor of 2 (Voltage ratio, 6 d. B Power) multipacting breakdown margin for less than 2 kg/m 2 areal density. Less than 15% (0. 7 d. B) 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/k. Wh delivered energy. 000323 rmd

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. 991025 rmd

SSP WPT Spatial & Spectral Interfaces Amplitude of Power Density, W/m 2 or Spectral Density, W/m 2/Hz Main Beam 1 st Grating Lobe Fundamental Sidelobe Envelope Rectenna Close-In Carrier Noise . . . Power Supply Ripple Modulation Dawn Trout IOM to Jeff Anderson MSFC 8/31/98: 3 rd Harmonic Sidelobe Envelope . . . Harmonic Envelope Fundam ental 2 nd 3 rd 4 th . . . 14. 896 -15. 121 GHz < -138 to -148 d. BW/m 2/4 k. Hz depending on arrival angle (pp. 275 Kobb Guide) PFD @ Earth in the Band 18. 6 -18. 8 GHz < -101 d. BW/m 2/ 200 MHz for all Angles ( pp. 268) NASA EMI Test Levels: Space Station. . . . . 60 V/m Shuttle & Shuttle P/L. . . 2 V/m GSFC Satellites. . . . . 5 V/m SAE J-1338 Automobiles. . . 200 V/m 5 th 6 th 2 X 5. 8=11. 6 (10. 68 -10. 7=RA 1 st Sidelobe R’cve Only, 3 X 5. 8=17. 4 10. 7 -11. 7=Fixed, (17. 3 -17. 7= 4 X 5. 8=23. 2 5 X 5. 8=29 (23 -23. 55= Fixed S/C Space- Fixed S/C (27. 5 -29. 5= 5. 8 GHz ISM=5. 725 -5. 875 GHz Earth) Earth-Space) Fixed, ISL, Fixed (5. 65 -5. 85=Radiolocation, Mobile) S/C E-S, Mobile, Amateur, ISM, Door Openers, PFD @ Earth in the Band LMDS) S. S. -Part 15 Devices, etc. ) MIL-STD-464 Design Levels: General Systems. . . . 310 V/m Shipboard & Ordnance. . . 1230 V/m Ground Systems. . . . 50 V/m Space & Launch Veh. . . . 200 V/m 2 nd Harmonic Sidelobe Envelope 5. 6 -5. 65 GHz=Maritime Radionavigation, Meteorological Aids, TDWR in ATC Rectenna Site Fence Boundary? MIL-STD-461 D EMC Tests: A/C External. . . . . 200 V/m Ship(Above Deck). . . 200 V/m Space. . . . 20 V/m (S Sp id ac elo e be s) ANSI/IEEE C 95. 1: Human Exposure @5. 8 GHz in an Uncontrolled Environment < 3. 87 m. W/cm 2 Averaged over 30 minutes. Controlled Environment <10 m. W/cm 2 Averaged over 6 minutes. . 7 th 8 th 9 th 10 th Ha rmonics . . . NASA Spectrum Manager, via Vern Heinen Le. RC: ITU-R SA-1157: -250 d. BW/m 2/Hz ITU-R RA-769: -240 d. BW/m 2/Hz > 1 GHz (Undisturbed Sun = -180 d. BW/Hz) (World Countries= 239) Note: Not to Scale Frequen cy (Spectru m Sideban ds) 980818 rmd

BEAMER Big Electromagnetic Array Microwave Energy Research Facility An Integrated Space Solar Power Test & Demonstration Facility by Richard M. Dickinson, JPL RADAR SCIENCE SYSTEM MODELING PERFORMANCE & $ SHADOW EFFECTS PV by DOE? ATMOSPHERE SCIENCE RECTENNAS for Commercial Platforms ANTENNA ACTIVE -TRUSS PATTERNS &A/C BEAM TURNER PMAD Interfaces, Instrumentation & Transients RF ARRAY ROBOT Phase Cal & Maintenance BEAM SAFETY RADARS 991101 rmd

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. 991020 rmd

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. 991021 rmd

BEAMER An Integrated Space Solar Power Test & WPT Demonstration Facility by Richard M. Dickinson, JPL BEAMER R BEAME 991205 rmd Big Electromagnetic Array Microwave Energy Research Facility

Mars Outpost Technology for Wireless Power Transmission Proposed Dust Buster Concept Study by Richard M. Dickinson, JPL Power-Efficiency Chain Design Control Table: Mars Terrain Outpost 150 m Rectenna and Coring Rover Beamer Facility 245 GHz 17, 000 km Aerosynch Orbit SSP 180 m Dia. Beamer (61 ea 20 m Dia Inflatables) 1. DC-80 k. V Conversion. . . . 0. 9 2. Typ. 200 k. W , 245 GHz Gyrotron. . . 0. 4 3. 20 m Array Element, /30 Surface Acc. . 0. 84 4. 20 deg. rms Phase Accuracy. . . . . 0. 88 5. Aperture/Feed Efficiency. . . 0. 65 6. Circle Pack Fill Factor G/L Losses. . . 0. 75 7. Beam Coupling Efficiency. . (-4 d. Btaper). . . 0. 63 8. Dust Attenuation for Optical Depth of 6, 10 km Scale Height, mean 20 micron dia. Particle & Dielectric Constant 2 -j 0. 4, at 245 GHz. . [1]. . . 0. 003 to 0. 383 d. B. . 0. 916 9. Rectenna Collection-Conversion Eff. . 0. 5 10. Output Power Conversion Efficiency. . . 0. 95 Overall DC in-DC-out Efficiency. . . 0. 0356 (e. g. for 100 k. W out, 2. 8 MW input from PV PMAD) [1] Smith, E. & Flock, W. , ”Propagation Through Martian Dust at 8. 5 and 32 GHz, ” TDA Progress Report 42 -87, pp. 291 -299, July-Sept. 1986. 990406 rmd

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? 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 Pilot Signal Safety Radars Retrodirective Phased Array Control Facility 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 000322 rmd