Theoretical and Experimental Studies of Atomic Oxygen Interacting with Material Surfaces in Low Earth Orbit

Transcription

1 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

2 1. Introduction 2. Experimental Studies of Atomic Oxygen Effects on Space Material Surfaces 3. Theoretical Modeling and Numerical Simulation 4. Concluding Remarks

3 I. INTRODUCTION Space environment: Highly complex Altitude of 200~700 km (LEO): atomic oxygen erosion highly oxidative environment ultraviolet radiation vacuum ultraviolet radiation

4 AO in LEO Pressure: 10-3 ~ 10-5 Pa Photochemical reaction 2 + hν 2 Number density ~ O (10 9 ) cm -3 Spacecraft orbital velocity approx. 8 km/s O Actual flux of AO impinging on orbiting vehicle approx. : ~ atoms/cm 2 -s Impact energy of AO onto spacecraft surface: 4.4~4.5 ev ± 1.0 ev O

5 Research on atomic oxygen effects on space materials at BUAA Experiments Numerical simulation

6 II. Experimental Studies of Atomic Oxygen Effects on Space Material Surfaces 2.1 Ground Test Facility for Simulating Space Environment Test facility for atomic oxygen effects Ultraviolet radiation system Vacuum ultraviolet radiation system AOE (Atomic Oxygen Effects) Test Facility 1. A hot cathode filament discharge plasma-type facility Consisting of several subsystems: Hot cathode filament discharge Surface-restrained multiple magnetic Parametric diagnostic subsystem

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8 2. Main components of the plasma: O,O,O,O,e Flux of atomic oxygen atoms/(cm 2 s) Flux of oxygen ions ions/(cm 2 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 (10 10 /cm 3 ). The magnetic field will decay rapidly away from the wall so that the flow field will not be influenced. 4. Effective cross-section ~ Φ20cm

9 2.1.2 Ultraviolet radiation (UV) experimental system Ultraviolet radiation source: Deuterium lamp Schematic diagram of UV radiation Experimental system Working principle of deuterium lamp

10 Radiation spectrum of deuterium lamp 1.2 Radiation Intensity ( W m -2 nm -1 ) D 2 Lamp Solar Wavelength (nm)

11 2.1.3 Vacuum ultraviolet radiation (VUV) Experimental system Vacuum ultraviolet radiation source: Krypton lamp Schematic diagram of VUV radiation experimental system

12 Operational parameters: wave length ~ 123.6nm, within the range of 121.6nm (space) and 130nm (ground) no. of photons: photons/(cm 2 s) >> photons/(cm 2 s) (VUV strength in space) Operating principle schematic diagram for krypton lamp

13 2.2 Effects of Atomic Oxygen on Space Materials Polymeric Materials 1. Kapton Before Test After Test

14 Scanning-electron-microscopic pictures of Kapton before and after AO exposure erosion under moderately large AO flux erosion under large AO flux

15 Optical parameters of Kapton (pre- and aft-tests) pre-experiment AO experiment ( R% ) Reflectivity Transmissivity ( T% ) pre-experiment AO experiment Wavelength ( nm ) 0 Wavelength (nm)

16 2. Teflon The appearance and optical parameters unchanged SEM pictures of Teflon before and after AO exposures Erosion due to low AO flux Erosion due to high AO flux

17 Mass loss and erosion of Teflon after AO exposures

18 2.2.2 Composite Materials 1. β cloth SEM pictures of β cloth before and after AO exposure Erosion due to low AO flux Erosion due to high AO flux

19 Mass losses and erosion rate of β cloth after AO exposure 1500 Volume Loss (10-5 cm 3 ) Kapton Teflon Beta cloth Volumetric losses of Kapton, Teflon, and β cloth in AO tests Experiment time (hours)

20 2. Glass Fiber/Epoxy SEM pictures of glass fiber/epoxy before and after AO exposure Erosion due to low AO flux Fibers Epoxy Erosion due to high AO flux Fibers Epoxy Fibers Epoxy

21 Mass losses and erosion rate of glass fiber/epoxy after AO exposure 1500 Volume Loss (10-5 cm 3 ) Kapton Glass/epoxy Volumetric losses of Kapton, and glass fiber/epoxy in AO tests Experiment time (hours)

22 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

23 Mass losses and erosion rate of carbon fiber/epoxy after AO exposure

24 2.3 Metal Silver Films 1. Appearance Erosion due to low AO flux Erosion due to high AO flux

25 SEM pictures of silver film before and after AO exposure Erosion due to low AO flux Erosion due to high AO flux

26 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

27 2. Teflon Mass losses of Teflon after coupled AO/UV exposure AO AO/UV

28 Appearance of Teflon before and after VUV radiation

29 Optical parameters of Teflon before and after coupled VUV/VUV/AO exposure Reflectance (R%) pre-experiment VUV experiment VUV+AO experiment Transmissivity (T%) pre-experiment VUV experiment VUV+AO experiment Wavelength (nm) Wavelength (nm) 80 Absorptance (a%) pre-experiment VUV experiment VUV+AO experiment Wavelength (nm)

30 3. βcloth Appearance of β cloth before and after VUV radiation

31 Optical parameters of β cloth before and after coupled VUV/VUV/AO exposure pre-experiment VUV experiment VUV+AO experiment Reflectance (R%) Transmissivity (T%) pre-experiment VUV experiment VUV+AO experiment Wavelength (nm) Wavelength (nm) Absorptance (a%) pre-experiment VUV experiment VUV+AO experiment Wavelength (nm)

32 2.4 Anti-Erosion Study on Spacecraft Materials Protection Coatings TO/Kapton Al/Kapton Au/Ag Pb-Sn/Ag

33 1. TO/Kapton Mass loss ~ 1/20 of Kapton Erosion due to low AO flux Erosion due to high AO flux

34 2. Al/Kapton Apperance, mass, and topographic nature are unchanged 3. Au/Ag Film Mass losses of Au/Ag film after AO exposure AO

35 4. Pb-Sn/Ag Mass losses of Pb-Sn/Ag film after AO exposure AO

36 2.4.2 Compound with organic silicon additive KH560( 3-Glycidoxypropyltrimethoxysilane) KH550( γ-aminopropyl triethoxy silane ) 3500 Mass Loss (10-5 g) Epoxy Mass Loss (10-5 g) Epoxy Atomic Oxygen Fluence (10 20 atom/cm 2 ) Atomic Oxygen Fluence (10 20 atom/cm 2 ) Mass loss of KH560/Epoxy Mass loss of KH550/Epoxy

37 2.4.3 Inorganic Grain Additive Materials 1. Appearance before and after OA exposure

38 Mass loss after AO exposure 3000 Mass Loss (10-5 g) Epoxy Mass Loss (10-5 g) Epoxy Experiment Time (hours) 1. Ultrafined hollow grains(2μm) 2. Nano-SiO 2 (25nm) Experiment time(hours) Mass Loss (10-5 g) Epoxy Atomic Oxygen Fluence (10 20 atom/cm 2 ) 3. Nano-Al 2 O 3 (50nm)

39 3. Topographic characteristics of Material Surfaces (1)Epoxy (2) Cenosphere/Epoxy (3)SiO 2 /Epoxy AO AO AO

40 III. Theoretical Modeling and Numerical Simulation 3.1 Theoretical Model Dynamic Model Interaction Potential Model Reaction Probability Model

41 3.1.1 Dynamic Model ( ) ( ) M s d Y / dt = V,,, M d / Y X Y Y Y Y dt+ f Y t E 2 E 2 I E F E E s γ incoming particle (X) reactive trajectory Z unreactive trajectory V > V < Y boundary (Y S ) X inner ( Y I ) fixed ( Y F ) M d2 dt2 g V X / = ( X, Y I, Y E, Y F X ) Md 2 YI/ dt 2 = V ( X, YI, YE, YF ) Geometric sketch of theoretical model s Y I

42 1. Dynamic Equations for Gas Particles Free molecular flows Mg X&& = X V X, Y, Y, Y ( ) I E F 2. Dynamic Equations for Particles in V < (Inner Zone) Standard molecular dynamics Ms Y&& = Y V X, Y, Y, Y ( ) I I I E F

43 3. Dynamic Equations for Particles in Edge Zone Follow a class of Langevin equations M sy && = V X, Y, Y, Y M sγ Y& + f t ( ) ( ) E Y E I E F E with additional isotropic local frictional γ =πω /6=πk θ /6h D Y E and Gaussian white-noise type random forcing terms f Y E (t) E = B B S D (2 γ k TM /h) E 1/2 ξ T Y () t fy (0) 2 (t)γ MSkBT1 < f >= δ 4. Fixed Zone ( V U V ) > < Unaffected by interaction Y E

44 3.1.2 Interaction Potential Model Incident AO Material surfaces Interatomic potential on material surfaces 1. Incident AO/Material Surface Base Potential o 2a( re r ) a( re r Vr ) ( ) = D e 2e e Model I (For metals, crystalline and polyethylene materials) ( ) ( ε ) ( ε ) =ε ε r r a ee r r 2a s e gs o ee V r D e 2 e

45 ε s ε e ε gs - correction factor to account for the interaction of an AO with multi-particles on the material surface - effective equilibrium-distance factor - weighting factor Model II (For polyethylene materials) o 2a( εere r ) a( εere r Vr ) ( ) = D e 2ε e e gs 2. Effective Interatomic Potential 2 4 ε + 2 U = h ω α Lif π 3 4R 6

46 3.1.3 Reaction Probability Model N r;e; R c θ P = i k R N r c ;E ; θ T i k N R N T - No. reactive trajectories - No. total trajectories θ - Incident angle of the incoming particle k accommodation coefficients (nonreactive trajectories) α= Ei Ef Ei 2k T B s 3.2 Numerical Procedure Standard Verlet algorithm

47 1. AO/graphite 3.3 Some Numerical Results AO/graphite AO/polyethylene AO/Kapton 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 θ D = 420K Depth of the potential well o o 1 De = Do + hω= 11.23eV 2 weak strong 3.40Å 1.42Å

48 Reactive Probability for AO/Graphite 0.30 P R θ (deg.) 0 PR PR PR LEO (STS46) θ P R ~ 34% Incident angle-dependence of reaction probability for ε s =14,ε =0.3 gs

49 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 θ D = 218K c Required reactive criterion = 0.686Å b a

50 Reactive Probability and energy accommodation coefficient for θ(deg.) P R α P R P R-LEO α (STS-46 ) P R ~ 14.3%

51 P R α θ θ Incident angle-dependence of reaction probability Incident angle-dependence of energy accommodation coefficient ε =3.0, Lε =0.098, ε r =4.12A s gs e e o

52 3. Kapton Miller index for the lattice surface of Kapton : (100) Calculations: for o 0 θ 70 o for 394 inner- monomers 897 edge fixed- o θ > inner- monomers 449 edge fixed- Initial velocities: Maxwell- Boltzmann distribution for T=310K Debye temperature θ D = 165 K Required reactive criterion = 0.686Å c b a

53 Reactive probabilities for different factors and STS-46 flight experiment ε e ε gs θ(deg.) PR P R PR-LEO

54 P R the calculted values cos 1.5 θ Incident angle-dependence of reaction probability coefficient ε =0.20, ε =2.9 gs Incident angle-dependence of energy accommodation coefficient e the calculated values α cos 0.7 θ θ θ

55 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

56 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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