overview on spacecraft charging study in japanoverview on spacecraft charging study in japan mengu...
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Overview on Spacecraft Charging Study in Japan
Mengu ChoMengu ChoLaboratory of Spacecraft Environment Interaction Engineering
Kyushu Institute of Technology
Koga Kiyokazu Koga, Hideki Koshiishi and Kumi NittaJapan Aerospace Exploration Agency
Acknowledgement: Colleagues in Japan
September 20, 2010
1
p ,11th Spacecraft Charging Technology Conference, Albuquerque, NM, USA
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Contents• Simulation study• Electrostatic discharge research in laboratoryElectrostatic discharge research in laboratory• Characterization of charging properties
P i f fli h i d• Preparation for flight experiment and demonstration
• In-orbit space environment measurement• Guideline
2
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MUSCAT Improvement
• Fast & Stabilized ComputationInternal Charging Sim lation• Internal Charging Simulation
• Plasma Environment DataA l El t E• Auroral Electron Energy Distribution Li St d Al• Linux Stand Alone
• Simulation of Charging Mitigation by NeutralizerMitigation by Neutralizer
• & etc.
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Charging Analysis of a Solar SailFor the Next-generation, Interplanetary-Flight Spacecraft
@1.0AU
IKAROS ©JAXA
Membrane: Al-coated PolyimideArea: 14x14(m2), Thickness: ~10-6(m)( ), ( )
S/C Charging & Charged Particle Profiles:For S/C & Payload Design
4Paper on Wednesday
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Charging Analysis of a Solar SailSolar Flux & Plasma flow: left to right, dx=0.5m, Plasma [email protected]
ambient electron ambient ion
photoelectron electric potentialp otoe ect o p
5Paper on Wednesday
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PIC Simulations of a Double-Probe Electric Field Sensor onboard Scientific Spacecraft Using the EMSES Codep g
Miyake, Y. (Kyoto Univ.), H. Usui (Kobe Univ.), and H. Kojima (Kyoto Univ.)
Application of space plasma PIC simulation to the analysis of time-
EMSES Code (Electro-Magnetic Spacecraft Environment Simulator)
dependent electromagnetic environment of scientific spacecraft
[Miyake and Usui, Phys. of Plasmas, 16, 062904, 2009]• Full PIC electromagnetic code• Modeling of spacecraft immersed in space plasmag p p p• Time-dependent spacecraft-plasma interactions including EM-field evolution
- Spacecraft charging, Plasma and EM-field environment around S/CEMSES simulation Linear theory
• Rectangular, uniform grid system • High performance computing by parallelization with domain decomposition
EMSES simulation Linear theoryre
quen
cy
parallelization with domain decomposition using MPI
Dispersion relation of EM sheath wave propagating along S/C surface
Fr
Wave number
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Bias current circuitBepiColombo/MMO to Mercury
Application of EMSES to simulations of a double-probe electric field sensor
~ 4 V100 101 V
ee e
Sensing element(nearly at a space potential)Spacecraft
Boom
e: photoelectron
4 V100 ~ 101 V
Guard electrode(negatively charged by reference to s/c)
StubMEFISTO: Electric field sensor
Structure of MEFISTODensity plot of photoelectrons
emitted by the s/c bodySunlight
•PIC simulations with EMSES
D i f h d l d
•PIC simulations with EMSES
D i f h d l d
s/c
Guard (-25V)
ProbeSunlight - Demonstration of the guard electrode
to repel PEs coming from the s/c body.
- PE behavior around the sensor
- Demonstration of the guard electrode to repel PEs coming from the s/c body.
- PE behavior around the sensor
Photoelectrons emitted by s/c body areeffectively repelled by the guard operation
- Study on the conditions for the guard electrode operation to repel the PEs effectively
- Study on the conditions for the guard electrode operation to repel the PEs effectivelyyy
Application to scientific payload design and data calibration
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Electrostatic discharge research in laboratory
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ESD test on solar array
http://www.spacechina.com/cpyjs wxyhtq Detai
• ESD tests on solar array continues at KIT based on ISO-11221 9
p p pyj _ y q_ls.shtml?recno=48130
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Flashover propagation experiment2 solar array panels with 2m x 1.2m
6
v=5.3t-0.5
gap: 6cm
Discharge point Poten
Propagate to 3m
ntial, kVV
Flashover jumped the gap
Joint experiment by KIT and JAXA
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Solar array ESD researches at KIT• Effect of temperature on arc rate• Effect of water molecule adsorption p
on arc rate• Aging effect• Arc initiation method• Secondary arc mitigation by current
Cracks observed in grouting after agingy g y
oscillation with capacitor and inductor
~100μ• Flashover simulator• Orbital demonstration of high
Needles
100μm
voltage solar array technology11
Solar cell
Primary arc triggerPapers in this conference
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ESD from electrically floating electrodes due to internal charging
E=7keV
-4500
-4000
0.1 mm thick poly-imide substrates with floating electrodes
Electrode 2
Electrode 1
Electrode 3
Electrode 5
0.1mm 1mm
m
40mm
4000
-3500
-3000
ntia
l (V
)
Electrode 3Electrode 2
Electrode 2 Electrode 3
Electrode 4
100m
m90m
m
80mm
mm
40m
m
-2500
-2000
-1500uraf
ace
Pot
en
Electrode 4
100mm
40m
2mm -1000
-500
S
S f 00 50 100 150 200
Time (min)Electrodes#2, #3: electrically floating#1 #5: grounded through electrometer
Time dependences of surface potentials of fl ti l t d i di t d ith l t
Shape of sample
12
#1, #5: grounded through electrometer#4, backing: grounded
floating electrodes irradiated with electron energy of 7keV and beam current density of 0.1 nA/cm2
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Characterization of charging propertiesCharacterization of charging properties
13
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Internal charge measurement in bulks using Pulsed Electro-Acoustic(PEA) method at TCU
PEA t・The internal charge accumulation and distribution in dielectrics can be observed using PEA method. PEA systemfor radiation
PI filmElectrode Electrode Electrode ElectrodePI film・Observed
NegativePositive
charge accumulation in the bulks of PI films irradiated by the Electron
Protonbeams.
The internal charge accumulation and distribution in dielectrics can be observed using PEA method.
50
(z) [
C/m
3 ]
5
10
15E-beam Proton-beam
z) [C
/m3 ]
-50
0
arge
Den
sity
(
-10
-5
0
rge
Den
sity
(z
Electron beam irradiation(80keV) Proton beam irradiation(2MeV)
-50
0 125
Cha
-15
10
0 125Position z [m]Position z [m]
Cha
Paper on ThursdayNow ,Developing the new internal & surface charge measurement system using improved PEA method.
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Electron beam induced charging of insulating materialsat Nara National College of Technology
1 E+19
125m silvered Teflon FEP
0
4000
0 5 10 15 20
Electron Energy (keV)
1.E+18
1.E+19
y (o
hm_m
)
-8000
-4000
0 5 10 15 20
ace
Pot
entia
l (V
)
E=2.7keV
1.E+17
1.E 18
lum
e R
esis
tivity
EII in SEE yield
-12000
8000
Sur
fa
Jb≒0.1nA/cm2
1.E+1616000 12000 8000 4000 0
Vo
3000-16000
-16000 -12000 -8000 -4000 0Surface Potential @60min (V)
3000
Electron energy dependence of surface potential in case of beam current density
Surface potential dependence of volume resistivity obtained from the charge decay
15
potential in case of beam current density Jb= 0.1 nA/cm2 for 60 minutes
resistivity obtained from the charge decay characteristics after electron irradiation.
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Characterization of charging properties of degraded material at KIT
S d l– Secondary-electron– Photo-electron
Volume and surface conductivity by charge storage method
Papers in this conference
– Volume and surface conductivity by charge storage method
conductivityAO
AO facility
16SEE & PEEUV
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Characterization campaign of charging properties of degraded material sponsored by
Material property The range of primary energy Place
Framework for the Measurements of Materials Properties ParameterJAXA
Secondary electron emission (SEE)
Accelerating voltage: 600V-5kV
The High Energy Accelerator Research Organization (KEK)
Accelerating voltage: 200V-1kV
JAXA &Tokyo City university
Photoelectron emission Wavelength 30 to 250 nm KEKPhotoelectron emission (PE)
Wavelength 30 to 250 nm KEK
Wavelength 110 to 400 nm Tokyo City universityBulk resistivity, ASTM D-257, JIS C2139 Saitama UniversitySurface resistivity
Bulk resistivity Charge storage method Saitama University
Di l t i C t t S it M t l T h l
17
Dielectric Constant Sumitomo Metal Technology Inc.
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Charging/discharging properties at EOLCharging/discharging properties at EOLCharging/discharging properties at EOLCharging/discharging properties at EOL
NASA Photo
Charging/dischargingCharging/discharging propertiesproperties ofof manymany materialsmaterialswerewere studiedstudied throughthrough collaborationcollaboration ofof JAXAJAXA andandT08216AC
100T08216AC
100T08216AC
100T08216AC
100
werewere studiedstudied throughthrough collaborationcollaboration ofof JAXAJAXA andandKobeKobe UniversityUniversity.. WellWell--characterizedcharacterized 88 km/km/ss atomicatomicoxygenoxygen beambeam waswas usedused forfor simulatingsimulating LEOLEO spacespaceenvironmentenvironment atat KobeKobe UniversityUniversity..Charging/dischargingCharging/discharging propertiesproperties ofof thethe simulatedsimulatedEOLEOL samplessamples werewere analyzedanalyzed byby JAXAJAXA andand SaitamaSaitamaU i itU i it
T08216ACNote: longitude is not devided by flight time
Inte
nsity
(cou
nts)
20
40
60
80Note: longitude is not devided by flight time
Inte
nsity
(cou
nts)
20
40
60
80
Approx. 8 km/s
T08216ACNote: longitude is not devided by flight time
Inte
nsity
(cou
nts)
20
40
60
80Note: longitude is not devided by flight time
Inte
nsity
(cou
nts)
20
40
60
80
Approx. 8 km/s
UniversityUniversity..
TOF distribution of oxygen atomTOF distribution of oxygen atom
Flight time (s)
-200 0 200 400 600 800 1000 1200 14000
Flight time (s)
-200 0 200 400 600 800 1000 1200 14000
TOF distribution of oxygen atomTOF distribution of oxygen atom
Flight time (s)
-200 0 200 400 600 800 1000 1200 14000
Flight time (s)
-200 0 200 400 600 800 1000 1200 14000
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t
Charge Storage Method for Volume Resistivity in Space Environment at TCU
• Vacuum and E-beam• Volume resistivity is calculated from the
d k d i k l
d
t
eVtV 0)(
dark current decay constant in week long surface potential history
Test parameters
Temperature charge residual at cryogenic temperature
Electron energy and flux range and dose effect (RIC)
Sample thickness E-field 1exp T
penhancement
19
*A.R. Frederickson and J.R. Dennison, IEEE Trans. on Nuc. Sci., Vol. 50, No. 6(2003)
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Conductivity Measurement in Vacuum using Conventional Method at TCU ・The conductivity of dielectrics for spacecraft is observed using the conventional method
(ASTM D257,JIS K6911)
10-14
Kapton-V真空Kapton V
Kapton in air atmosphereKapton in vacuum
(ASTM D257,JIS K6911)
・We confirm that the PI’s conductivity decrease in vacuum condition.
M t t
10-16
10-15
電率
[S
/m]
真空Kapton-V
Ohmic low
Kapton in vacuum
uctiv
ity
[S/m
]
Child low
Measurement electrode system
Vacuum chamber
Measurement system
20 40 60 80 100 120 140 16010-17
10
電界 E [kV/mm]
導電
Applied Electric Filed E [kV/mm]
Con
du
Child low
10-15
10-14
/m]
Apical-NPI真空Apical-NPI
Apical in air atmosphereApical in vacuum
m] Ohmic low
電界 E [kV/mm]Applied Electric Filed E [kV/mm]
Current
HV
10-16
10
導電率
[S
/C
ondu
ctiv
ity
[S/m
Digital electro mater
20 40 60 80 100 120 140 16010-17
電界 E [kV/mm]Applied Electric Filed E [kV/mm]
C
High Voltage Power Supply
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Lunar Dust Charging• Experiment on dust charging and subsequent levitation
21Poster in this conference
Joint work of KIT and USC
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Preparation for flight experiment and demonstration
22
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Development of surface charging sensor• Application of COTS potential monitor to
satellite surface potential monitor
Trek 820 potential meter Environment test modelTrek 820 potential meter Environment test model•Conversion of ultra-high impedance contact-type•Sensor head as small as 1mm or less
23
•Mulitple-sensor head to measure deep dielectric charging
Poster in this conference
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Spacecraft Charging Mitigation
• Electron-emitting Film for Spacecraft Charging Mitigation (Elf’s CHARM)g ( )– To be launched in as early as Nov. 2011
• Semi-conductive transparent coatingSemi-conductive transparent coating Space plasma (potential reference)
Energetic ee e
gelectrons
++
+
++
++
++++++Field emitted electrons
Cupper
Spacecraft chassis ( )Conductive
+++++Polyimide
ELF/GEO ELF/PEO
Space potential
(metal)Conductive adhesivePolyimide/Copper Fluorine Polymer/Copper
Paper in this conference
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Electrodynamic bare tether• Preparation for orbital demonstration on a small
satellite– Field Emission Cathodes using Carbon Nanotube
(Paper on Thursday)( p y)– Arc suppression (poster in this conference)
25Bare tether sampleEDT Discharge positions
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PASCAL (Primary Arcing effects on Solar Cells at LEO)
• To be launched to ISS in February 2011– Characterize solar cell degradation due to arcing– Active experiment with COTS-based electronics for biasing
cells and collecting data
http://iss.jaxa.jp/iss/ulf3/mission/overview/eva/eva3/
PASCAL electronics box
26
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In-orbit space environment measurement
27
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Instruments onboard (LEO) GOSAT
S di ti i tISSSpace environment data acquisition
instruments (SEDA-AP)
Space radiation environment detectors (TEDA/ LPT)
ISS
JASON-2
Space radiation en ironment
ALOS
28
Space radiation environment detectors (TEDA/ SDOM)
Space radiation environment detectors (TEDA/ LPT)
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Instruments onboard (GEO)
DRTSETS8
Space environment monitors (TEDA/MAM,POM)
Space radiation environment detectors (TEDA/ SDOM)
( )
QZS-1
29Space environmental monitors (TEDA/LPT, MAM, POM)
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Spacecraft charging design guideline• JERG-2-211 “Satellite Design Guideline for Charging
and Discharge”– Published in 2009– Characterization Campaign
• Material data for charging simulation• Solar array secondary arcy y
30