14      !
Daniel Hastings and Henry Garrett,“Spacecraft-Environment Interactions”

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!#e-H+$"©JAXA

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• 
200310
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8•– •  ––  11• ! –  !  #• ')&(• ""$%
*+
– – #12



I net (φ s )φsSpacecraftSpacedQ= I netdt

Q = Csφ sCsdφ s 1= I netdt Csdφ s= 0  I net (φ s ) = 0dt
13

 : Isi
: Ii
: Ie: Ibe

: IseCsSunlight: Iph

Inet= Ii + Ise + Isi + Ibe + Iph - Ie14•   LEO (Low Earth Orbit)– 300 km1500 km
90 8 km/s–•   GEO (Geosynchronous Orbit)– 36000 km   (ISS)–
1400 km
36000 km6380 kmEarth15GEO keVkeV

NominalWorst

ElectronIon

n1

106 m-30.78±0.7

0.19±0.16

T1keV

0.55±0.32

0.8±1.0n2

106 m-30.31±0.37

0.39±0.26

T2keV

8.68±4.0

15.8±5.0

n1

106 m-3

1.00

1.10

T1keV

0.6

0.4

n2

106 m-3

1.40

1.70

T2keV

25.1

24.7

16

 GEO

dφ s 1
1= I net = ( Ii − Ie + I se + I be + I ph )
dt Cs
Cs

j ph > je > ji
10-5

10-7~10-6 10-8~10-7

Iph 

Ie

Inet > 0A/m2=>φs > 0

Inet < 0 =>φs < 017 GEOd (φ d − φ s ) 1
σd=ji − je + jse + jbe + j ph ) −(φ d − φ s )(dtCdεd j ph = 012
Al 0.97@300
Kapton 2.1@150V
Teflon 3@300V
Coverglass 11@800V

106d (φ d − φ s )
>0dt

4
200

2000

4000

6000

8000

Ee, eV10000

Time

Potentialδe8

jse > je 

φs < 0DielectricSatellitePotential difference

Inverted potential gradient20

Mechanism of arcinge-Secondaryelectroneee-e-Electronbeamee-e-             

Cover glass
Interconnector
Cell
RTV
Triple junction
Kapton
CFRP

Charging ofcoverglass surface

Emission of electronfrom triple junction
due to EFEE

Charging of side edgeof coverglass

Substrate

Arc21

LEO


10101012 m-3
0.2 eV
105 m/s 103 m/s
22
15
 400km  (JEM)





ISS
23 LEO
"$ji << je
10~100µA/m2

$…
Solar array
VElectrons

Photoelectrons

1~10mA/m2

Plasma potential

$$
"

BodyIons#$"!

24

e-i+e-i+Coatingn200~300µm

CellCellee-ne-i+ni+++++++++++++++++++++++++++++i+

nni+i+e-i+ne-

Plasmai+i+e-

Coverglass
100~200µm
10~30µm
100µm

Substrate Interconnector
Adhesive
Triple junction＋ー25         

Solar array

VElectrons
Photoelectrons

Generating voltage
Plasma potential
Body

Ions

Plasma contactor

26
28

 PEO
"LEO'+ GEO'

LEO 10 keV .! % Wake* ($),+# > &+#φs ≈ 0  φd < 0/.-normal potential gradient30 PEO
…

ram  

φs < 0φd − φs > 0wake  φs < 0

φd − φs > 0

31•  • •   









32

B0>?<DFA)3'GA)@
E,+IR
56F(A)
$-.Al8

G:CA;
EA%4A1*"7)

<D/)(TREK)

2(&)

X-Y9# =!
"0.6m 0.9m 30keV#300µA

210-4Pa

 

400 l/s  !

0.7µm

 

260mm(FWHM)

85mm(FWHM)'

+ISO-11221,“Space systems -- Space solar panels -- Spacecraft
charging induced electrostatic discharge test methods”•••

  "%!$+# +&)* '+(*34JERG-2-211A •  !







Current, A

43

2



10
020

4060

Voltage, V

8010035

ISO-19923,“Space environment (natural and artificial) —Plasma environments for generation of worst caseelectrical potential differences for spacecraft”•  





36

(2003)0238 (2006)

(2006)

1999)(2008)7(2006)

(2005)(2008)

INSAT
©ISRO

GCOM(2010))

http://www.ssloral.com/html/satexp/telstar.html(

http://www.spacechina.com/cpyjs_wxyhtq_Details.shtml?recno=48130

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