theoretical and experimental studies of atomic oxygen interacting with material surfaces in low...
TRANSCRIPT
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Theoretical and Experimental Studies of Atomic Oxygen Interacting with Material Surfaces in Low Earth Orbit
Chun-Hian Lee
Zhigang Shen
Laiwen Chen
Xiaohu Zhao
2006
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1. Introduction
2. Experimental Studies of Atomic Oxygen Effects on Space Material Surfaces
3. Theoretical Modeling and Numerical Simulation
4. Concluding Remarks
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I. INTRODUCTION
Space environment: Highly complex
Altitude of 200~700 km (LEO): atomic oxygen erosion – highly
oxidative environment ultraviolet radiation vacuum ultraviolet radiation
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AO in LEO Pressure: 10-3 ~ 10-5 Pa
Photochemical reaction
Number density ~ O (109) cm-3
Spacecraft orbital velocity approx. 8 km/s Actual flux of AO impinging on orbiting vehicle approx. : 1014 ~ 1015 atoms/cm2-s
Impact energy of AO onto spacecraft surface:
2 2h O O
4.4~4.5 eV 1.0 eV
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Research on atomic oxygen effects on space
materials at BUAA Experiments Numerical simulation
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2.1 Ground Test Facility for Simulating Space Environment
Test facility for atomic oxygen effects Ultraviolet radiation system
Vacuum ultraviolet radiation system
2.1.1 AOE (Atomic Oxygen Effects) Test Facility
1. A hot cathode filament discharge plasma-type facility
Consisting of several subsystems:
Hot cathode filament dischargeSurface-restrained multiple magnetic Parametric diagnostic subsystem
II. Experimental Studies of Atomic Oxygen Effects on Space Material Surfaces
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2. Main components of the plasma:
Flux of atomic oxygen 1017 atoms/(cm2·s) Flux of oxygen ions 1014 ions/(cm2·s)
3. Large number of pairs (with opposite poles) of permanent magnets placed on the boundary of vacuum chamber to confine the plasma to increase the density of the electrons (1010/cm3).
The magnetic field will decay rapidly away from the wall so that the flow field will not be influenced.
4. Effective cross-section ~ Φ20cm
+ +2 2O , O , O, O , e
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2.1.2 Ultraviolet radiation (UV) experimental system
Working principle of deuterium lamp
Schematic diagram of UV radiation Experimental system
Ultraviolet radiation
source: Deuterium lamp
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Radiation spectrum of deuterium lamp
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2.1.3 Vacuum ultraviolet radiation (VUV) Experimental system
Vacuum ultraviolet radiation source: Krypton lamp
Schematic diagram of VUV radiation experimental system
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Operational parameters:
wave length ~ 123.6nm, within the range of 121.6nm (space) and 130nm (ground) no. of photons: 5×1014 photons/(cm2·s) >> 4×1011 photons/(cm2·s) (VUV strength in space)
Operating principle schematic diagram for krypton lamp
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2.2 Effects of Atomic Oxygen on Space
Materials
2.2.1 Polymeric Materials
1. Kapton
Before Test After Test
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Scanning-electron-microscopic pictures of Kapton before and after AO exposure
erosion under moderately large AO flux erosion under
large AO flux
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Optical parameters of Kapton (pre- and aft-tests)
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2. Teflon The appearance and optical parameters unchanged
Erosion due to low AO flux
SEM pictures of Teflon before and after AO exposures
Erosion due to high AO flux
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Mass loss and erosion of Teflon after AO exposures
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2.2.2 Composite Materials
2000×
1000×
2000×
1. β cloth
SEM pictures of cloth before and after AO exposure
Erosion due to low AO flux
Erosion due to high AO flux
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Mass losses and erosion rate of β cloth after AO exposure
Volumetric losses of Kapton, Teflon, and β cloth in AO tests
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2. Glass Fiber/Epoxy SEM pictures of glass fiber/epoxy before and
after AO exposure
Fibers Epoxy
Fibers Epoxy Fibers Epoxy
Erosion due to low AO flux
Erosion due to high AO flux
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Mass losses and erosion rate of glass fiber/epoxy after AO exposure
Volumetric losses of Kapton, and glass fiber/epoxy in AO tests
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3. Carbon Fiber/Epoxy SEM pictures of carbon fiber/epoxy before
and after AO exposure
Erosion due to low AO flux
Erosion due to high AO flux
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Mass losses and erosion rate of carbon fiber/epoxy after AO exposure
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2.3 Metal Silver Films
1. Appearance
Erosion due to low AO flux
Erosion due to high AO flux
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SEM pictures of silver film before and after AO exposure
Erosion due to low AO flux
Erosion due to high AO flux
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2.2 Coupled AO/UV/VUV Effects on Spacecraft Materials
1. Kapton
Kapton would maintain its appearance, mass, surface characteristics and optical parameters unchanged under the action of UV and VUV radiation AO effects on Kapton maintain unchanged under the coupling UV /VUV effects
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2. Teflon
AO AO/UV
Mass losses of Teflon after coupled AO/UV exposure
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Appearance of Teflon before and after VUV radiation
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Optical parameters of Teflon before and after coupled VUV/VUV/AO exposure
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3. βcloth
Appearance of β cloth before and after VUV radiation
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Optical parameters of β cloth before and after coupled VUV/VUV/AO exposure
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2.4 Anti-Erosion Study on Spacecraft Materials
2.4.1. Protection Coatings
TO/KaptonAl/KaptonAu/AgPb-Sn/Ag
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1. TO/Kapton
Mass loss ~ 1/20 of Kapton
Erosion due to low AO flux
Erosion due to high AO flux
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2. Al/Kapton Apperance, mass, and topographic nature are unchanged
3. Au/Ag FilmMass losses of Au/Ag film after AO exposure
AO
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4. Pb-Sn/Ag
Mass losses of Pb-Sn/Ag film after AO exposure
AO
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2.4.2 Compound with organic silicon additive
Mass loss of KH560/Epoxy Mass loss of KH550/Epoxy
KH560 ( 3-Glycidoxypropyltrimethoxysilane ) KH550 ( γ-Aminopropyl triethoxy silane )
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2.4.3 Inorganic Grain Additive Materials
1. Appearance before and after OA exposure
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2. Mass loss after AO exposure
1. Ultrafined hollow grains ( 2μm ) 2. Nano-SiO2 ( 25nm )
3. Nano-Al2O3 ( 50nm )
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3. Topographic characteristics of Material Surfaces
( 1 ) Epoxy ( 2 ) Cenosphere/Epoxy ( 3 ) SiO2/Epoxy
AO AO AO
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III. Theoretical Modeling and Numerical Simulation
3.1 Theoretical Model Dynamic Model Interaction Potential Model
Reaction Probability Model
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V<
V>
inner ( YI )
boundary( YS )
fixed ( YF )
Y
Z
X
incoming particle (X)
reactive trajectory
unreactive trajectory
Geometric sketch of theoretical model
2 2/ , , , I E FM d dt Vg XX X Y Y Y 2 2/ , , , I I E FI
M d dt Vs Y X Y Y YY
2 2/ , , , /E I E F EE E
M d dt V M d dt ts s Y X Y Y Y Y fY Y
3.1.1 Dynamic Model
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1. Dynamic Equations for Gas Particles Free molecular flows
I E FM V , , ,g
XX X Y Y Y
2. Dynamic Equations for Particles in V< (Inner Zone)
Standard molecular dynamics
I I E FIM V , , ,s
YY X Y Y Y
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3. Dynamic Equations for Particles in Edge Zone
Follow a class of Langevin equations
with additional isotropic local frictional
E I E F EE EM V , , , M ts s
Y YY X Y Y Y Y f
and Gaussian white-noise type random forcing terms
DD B/ 6 k / 6
E E
1/ 2B S(t) (2 γ k TM /h)Y Yf
E E
TS B( ) (0) 2 ( t)γ M k Tt
Y Y 1f f
4. Fixed Zone ( )
Unaffected by interaction> <V V
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3.1.2 Interaction Potential Model Incident AO – Material surfaces Interatomic potential on material surfaces
o e ee
2a r r a r rV r D e 2e
Model I (For metals, crystalline and polyethylene materials)
e e e er r a r r 2aos e gsV r D e 2 e
1. Incident AO/Material Surface
Base Potential
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Model II (For polyethylene materials)
o e e e ee gs
2a r r a r rV r D e 2 e
2. Effective Interatomic Potential
224 3 0 2ULif 63 4R
s
e
- correction factor to account for the interaction of an AO with multi-particles on the material surface- effective equilibrium-distance factor
gs - weighting factor
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3.2 Numerical Procedure Standard Verlet algorithm
3.1.3 Reaction Probability Model
N r ;E ;cR i kPR N r ;E ;cT i k
RN - No. reactive trajectories- No. total trajectories TN k - Incident angle of the incoming particle
accommodation coefficients (nonreactive trajectories)
i fE EiE 2k TsB
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3.3 Some Numerical Results AO/graphite
AO/polyethylene
AO/Kapton
1. AO/graphite
strong
weak
3.40Å
1.42Å
Miller index of the graphite surface: (100) Calculations uses: 105 inner atoms, 228 edge atoms, 2117 fixed atoms. Initial velocities: Maxwell-Boltzmann distribution for T=394K Debye temperature Depth of the potential well
Dθ = 420K
o oe o
1D D 11.23eV
2
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gss = 14, ε = 0.3ε
0 10 20 30 40 50 60 70 800.00
0.05
0.10
0.15
0.20
0.25
0.30
PR
Incident angle-dependence of reaction probability for
Reactive Probability for AO/Graphite
.)(deg RP RP LEORP
0 0.231
0.168
(STS46)
0.125
10 0.246
20 0.217
30 0.196
40 0.167
50 0.140
60 0.135
70 0.156
80 0.028
∆PR ~ 34%
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a
b
c
2. AO/polyethylene
Miller index of the polyethylene surface: (100) Calculations uses: 50 inner repeat units 97 edge repeat units 867 fixed repeat units Initial velocities: Maxwell-Boltzmann
distribution for T=310K Debye temperature
Required reactive criterion = 0.686Å Dθ = 218K
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0 10 20 30 40 50 60 70 80
0.383 0.371 0.337 0.255 0.210 0.141 0.093 0.072 0.084
0.8816 0.8444 0.8452 0.7791 0.7553 0.6900 0.5913 0.4880 0.4581
0.216
0.189 (STS-46 )
0.6823
θ(deg.)
RP
α
RP
R-LEOP
α
Reactive Probability and energy accommodation coefficient for
∆PR ~ 14.3%
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Incident angle-dependence of reaction probability
o
ε = 3.0, ε = 0.098, ε r = 4.12As gs e e
0 10 20 30 40 50 60 70 800.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.40
PR
0 10 20 30 40 50 60 70 800.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
Incident angle-dependence of
energy accommodation coefficient
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3. Kapton
c
b
a
Miller index for the lattice surface of Kapton : (100) Calculations:
for
394 inner- monomers 897 edge- 2579 fixed- for
10 inner- monomers 449 edge- 3411 fixed-
Initial velocities: Maxwell- Boltzmann distribution for T=310K Debye temperature
Required reactive criterion = 0.686Å
Dθ = 165 K
o o0 θ 70
oθ 70
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0 0.335 0.256 0.267 0.261 0.28 0.338 0.218
10 0.327 0.262 0.253 0.258 0.29 0.322 0.229
20 0.288 0.238 0.229 0.242 0.243 0.303 0.191
30 0.241 0.23 0.228 0.221 0.219 0.251 0.167
40 0.233 0.154 0.173 0.205 0.198 0.185 0.13
50 0.161 0.127 0.115 0.148 0.187 0.157 0.074
60 0.105 0.065 0.084 0.093 0.135 0.077 0.05
70 0.084 0.042 0.05 0.056 0.126 0.048 0.017
80 0.029 0.013 0.019 0.035 0.09 0.0 0.002
0.2003 0.1541 0.1576 0.1688 0.1964 0.1868 0.1198
2.9 3.0 3.0 3.0 3.0 2.9 3.1
0.2 0.2 0.25 0.35 0.68 0.0 0.2
eε
gsε
θ(deg.) RP
RP
R-LEOP 0.2409
Reactive probabilities for different factors and STS-46 flight experiment
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0 10 20 30 40 50 60 70 800.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35 the calculted values
cos1.5
PR
gs eε = 0.20, ε = 2.9
0 10 20 30 40 50 60 70 800.02
0.04
0.06
0.08
0.10
0.12
0.14
0.16
0.18
0.20 the calculated values
cos0.7
Incident angle-dependence of energy accommodation coefficient
Incident angle-dependence of
reaction probability coefficient
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IV. Concluding Remarks
1. Conclusions: Progresses
experimental and theoretical analyses crystalline materials (metals, nonmetals) polymeric materials effective interatomic potential – based meanfield theory
Difficulties More reliable interactive potentials are needed for diff. materials
theoretical model + experimental measurements Development of engineering models for evaluating the AO erosion of space materials
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2. Undergoing Work
Experimental : protection material evaluation and selection
Theoretical: reaction-diffusion equation modeling
further study on interactive potential modeling
3. Future Work
interactive potential modeling —— experimental + theoretical
theoretical modeling of combined effects on AO+UV radiation
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