02 Interaction Materials Environments

Materials and Processes DivisionESA/ESTEC/TOS-QM

Sheet: 1

The ESA SME Initiative Training Courses

The Spacecraft Environment The Spacecraft Environment The Spacecraft Environment The Spacecraft Environment and Materials Interactionand Materials Interactionand Materials Interactionand Materials Interaction

Marc Van EesbeekHead Materials Physics and Chemistry Section

Materials and Processes DivisionESA/ESTEC/TEC-QM

TEC/QMC 2


Introduction

On-ground Environment

Launch Environment

Space Environment


TEC/QMC 3


On- Ground

Temperature

Humidity

Atmosphere

Biological

Transport loads

Test


TEC/QMC 4


Launch and Ascent

Vibrations

Accelerations

Shocks

Thermal flux

Lightening impact

Rain

Birds0

1

2

3

4

5

0 200 400 600 800 1000 1200

Time (s)

1/2 separation2/3 separation

Solid Boosters burn outLiquid Booster burn out

3rd stage Cut Off


TEC/QMC 5


In Flight

e -, p +, X-ray, hνννν

Micrometeoroid

Cosmic raysDebris

temperatureVacuumRadiationSpace DebrisMicrometeoritesAtomic Oxygen


TEC/QMC 6



TEC/QMC 7



TEC/QMC 8


NUMEROUS PROBLEMSMAINLY DIMENSIONAL STABILITY

AND LUBRICATION

CHANGE IN OPERATIONALPROPERTIES OF

MATERIALS

OUTGASSINGVACUUM

GAS CLOUD

PERTURBATION OFMEASUREMENTS

NUMEROUS PROBLEMSESPECIALLY ON

SCIENTIFIC SATELLITES

CORONA

ARC

ELECTRICALPROBLEMS

CONDENSATION

MODIFICATION THERMO-OPTICAL

PROPERTIES

MODIFICATION RADIATIONEFFECTS

MODIFICATION ELECTRICALPROPERTIES

THERMALPROBLEMS

ELECTRICALPROBLEMS

( SEE “RADIATION”)

( SEE“TEMPERATURE”)

Space Environment Effects : Vacuum


TEC/QMC 9


Pressure as function of height

Altitude(Km)

Pressure(mbar)

KineticTemperature(K)

Gaseous Density(particles/cm3)

Composition

Sea Level 1013 ~300 2.5x1019 78%N2,21%O2,1%Ar

30 10 ~173 4x1017 N2,O2,Ar200 10-6 ~1200 1010 N2,O,O2,O+

800 10-9 ~1300 106 O,He,O+,H6500 10-13 103 H+,H,He+

22000 <10-13 101-102 85% H+, 15%He2+


TEC/QMC 10


NUMEROUS PROBLEMSMAINLY DIMENSIONAL STABILITY

AND LUBRICATION

CHANGE IN OPERATIONALPROPERTIES OF

MATERIALS

OUTGASSINGVACUUM

GAS CLOUD


NUMEROUS PROBLEMSESPECIALLY ON


CORONA

ARC

ELECTRICALPROBLEMS

CONDENSATION

MODIFICATION THERMO-OPTICAL

PROPERTIES

MODIFICATION RADIATIONEFFECTS

MODIFICATION ELECTRICALPROPERTIES

THERMALPROBLEMS

ELECTRICALPROBLEMS

( SEE “RADIATION”)


Space Environment Effects : Vacuum


TEC/QMC 11



TEC/QMC 12



TEC/QMC 13



TEC/QMC 14



TEC/QMC 15


Space Environment Effect : Radiation

NUMEROUS PROBLEMSPARTICULARLY ON



MODIFICATION OF THE ELECTRICALCHARGE STATE/ SURFACE CHARGINGINCREASED

OUTGASSING

MODIFICATION ATMOLECULAR LEVEL

MODIFICATIONTHERMO-OPTICAL

PROPERTIES

THERMAL PROBLEMS

RADIATION(VV, PROTONS,ELECTRONS)

INCREASED SENSITIVITY

MODIFICATION MECHANICALPROPERTIES

BREAKDOWN ELECTRICALPROBLEMS

FRACTURES (THINSTRUCTURES UNDER

STRESS)

(SEE “VACUUM”)

( SEE “TEMPERATURE” )

( SEE “ATOX” )


TEC/QMC 16


High Energy Solar Flux

Type Wavelength(nm)

Average Flux(W/m2)

Worst CaseFlux (W/m2)

Near UV 180-400 118 177

UV <180 2.3x10-2 4.6x10-2

FUV 100-150 7.5x10-3 1.5x10-2

EUV 10-100 2x10-3 4x10-3

X-rays 1-10 5x10-5 1x10-4

Flare X-rays 0.1-1 1x10-4 1x10-3


TEC/QMC 17


Particle Radiation

Orbit Fluence [J.m-2. Year-1] Absorbed Dose in 4 µm Al(Gy.year-1)

Electrons Protons Total Electrons Protons TotalMIR;LEO;350;

51,6;C4.6x102 11 4.7x102 6.4x102 1.5x101 6.6x102

ISS;LEO;426;51.6;C

8.6x102 36 9.0x102 1.2x103 4.8x101 1.2x103

GEO;35790;0;C

9.8x105 3.8x104 1x106 5.4x105 8.3x106 8.8x106

GLON;19100;64.9;C

8.3x105 2.6x105 1.1x106 3.8x105 2x106 2.4x106

HEO;500-39660;65;E

4.9x105 6.8x104 5.6x105 2.6x105 3.1x105 5.7x105

POL;LEO;600;97;C

2.3x103 1x102 2.4x103 2.5x103 3.0x102 2.8x103


TEC/QMC 18


Charged Particles Environment

Radiation Source Nature Energy Flux(part.cm-2s-1)

Characteristics Remarks

Galactic CosmicRays

Protons (~90%)α(He-nucleus) &Heavy Ions (10%)

10-2 GeV-1010 GeV 2-5 Least Significant formaterials

Solar Wind Protons (96%)α and O-ionsElectrons

~ 1KeV~ 1 KeV~20-40 eV

p+ 2.108 at 1A.U. - Neutral plasma- Low energy restricts hazards

to surface

No influence oncircumterrestrial orbits ataltitudes<6.6 RE

Solar CosmicEvents (Flares)

Protons (95%)Heavy Ions

1-100 MeV(below 10 MeVspectrum ~E-1..2,beyond ~E-5)

Precise predictionof solar activitycannot be made

- E and N particles varies byevents

- Omnidirectional isotropic

Trapped Radiation1.Inner Belts (1.2-3.2 RE)

2.Outer Belts(3-7 RE)

Protons andelectrons

Protons andelectrons

Ep+ < 30 MeV (90%)Ee- < 5MeV (90%)

All Ep+<1MeV

p+ 5.105 E>1 MeVe- 2.107 E>.5MeV

p+ 109 E>10KeVe- 5.2.107 e-5xE

with E in MeV

- Omnidirectional Isotropic- Flux varies with magnetic

latitude- Spectra are very variable

with solar activity (GEO)- Fluxes not entirely

symmetric in Longitude(SAA for protons)

- Most important for orbitsat altitude <6.6 RE

- High E protons in innerbelts only- Atomic displacements arepossible at LEO in SAA

Aurora Electrons andprotons

e- 2KeV<E<20 KeVp+ 80<E<800 KeV

e- 1010 duringstormsp+ <107

- Observed between 65o and70o N and S magneticlatitude at altitudes between100 and 1000 km

- Very much time dependent


TEC/QMC 19


Space Environment Effect : Radiation

NUMEROUS PROBLEMSPARTICULARLY ON



MODIFICATION OF THE ELECTRICALCHARGE STATE/ SURFACE CHARGINGINCREASED

OUTGASSING

MODIFICATION ATMOLECULAR LEVEL

MODIFICATIONTHERMO-OPTICAL

PROPERTIES

THERMAL PROBLEMS

RADIATION(VV, PROTONS,ELECTRONS)

INCREASED SENSITIVITY

MODIFICATION MECHANICALPROPERTIES

BREAKDOWN ELECTRICALPROBLEMS

FRACTURES (THINSTRUCTURES UNDER

STRESS)

(SEE “VACUUM”)


( SEE “ATOX” )


TEC/QMC 20


White paints

Coating ααααs initial ∆α∆α∆α∆αs after 1100e.s.h.

∆α∆α∆α∆αs after 1100e.s.h. + e- +p+

PSB 0.135 0.025 0.20

SG120FD 0.2 0.042 0.145

PSBN 0.16 0.010 0.11

SG121FD 0.154 0.011 0.078

PCBE 0.23 0.003 0.063

PCBZ 0.19 0.03 0.17

Z93P 0.136 0.025 0.094

S13GP6N 0.20 0.021 0.193


TEC/QMC 21


SSM and Flexible Solar Reflectors (RSF)

Material ααααs∆α∆α∆α∆αs after 1100

e.s.h. UV∆α∆α∆α∆αs after 1100

e.s.h. UV + e- +p+

RSF-R on Al 0.126 - 0.003 0.06

RSF-F on Al 0.132 -0.007 0.058

RSF-F C on Al 0.137 0.002 0.07

SSM FEP 125µµµµm /Ag 0.07 0.01 0.03

SSM FEP 25µµµµm 0.153 .025 0.04

MAPATOX K 0.42 0.009 0.026


TEC/QMC 22


Effect contamination on Solar Absorption


TEC/QMC 23


Solar Absorptance in Flight Data


TEC/QMC 24


Effect of Radiation on Tensile strength of Mylar


TEC/QMC 25


Radiation Sensitivity of Polymers

PTFE

FEPFilled Siloxanes

Unfilled Siloxanes

Polyimides

Nylon

Polyurethane

PolyethyleneMinor Noticeable Significant

Absorbed dose (Gy)105 106 107


TEC/QMC 26



TEC/QMC 27



TEC/QMC 28


Space Environment Effects : Temperature

(SEE “VACUUM” )

INCREASED OUTGASSING

MOLECULARDEGRADATION

HIGH

CYCLING

LOW

INCREASEDCONDENSATION

TEMPERATURE

MODIFICATIONELECTRICAL PROPERTIES

MODIFICATIONMECHANICAL PROPERTIES

THERMALMECHANICAL

FATIGUE

DEGRADATION OF OPERATIONALPROPERTIES OF MATERIALS

DEBONDING

FRACTURES/CRACKS

LOSS OF PROTECTIVECOATING

MODIFICATION CHARGESTATE

( SEE “VACUUM”)

EMBRITTLEMENT

(SEE “ATOX”)

(SEE“RADIATIONS”)


TEC/QMC 29


Equilibrium surface temperaturesMercury, Venus, Earth orbits

Surface Temperature (sun facing)

-1 00 .0 0

0 .0 0

1 00 .0 0

2 00 .0 0

3 00 .0 0

4 00 .0 0

5 00 .0 0

0 .05 0 .15 0 .2 5 0 .3 5 0 .4 5 0 .5 5 0 .6 5 0 .7 5 0 .85 0 .95

Alpha/Epsilon ratio

[deg

C]

T celsius 1AU T celsius 0.47 AU Mercury ap

T celsius 0.31 AU Mercury per T celsius 0.72 Venus


TEC/QMC 30


Thermo-0ptical Properties of Coatings

0 0.2 0.4 0.6 0.8 1

Thermo optical comparison

MetalOSRFEPKaptonBlack PaintWhite Paint

0

0.2

0.4

0.6

0.8

1

εH

αs


TEC/QMC 31


Space Environment Effects : Temperature

(SEE “VACUUM” )

INCREASED OUTGASSING

MOLECULARDEGRADATION

HIGH

CYCLING

LOW

INCREASEDCONDENSATION

TEMPERATURE

MODIFICATIONELECTRICAL PROPERTIES

MODIFICATIONMECHANICAL PROPERTIES

THERMALMECHANICAL

FATIGUE

DEGRADATION OF OPERATIONALPROPERTIES OF MATERIALS

DEBONDING

FRACTURES/CRACKS

LOSS OF PROTECTIVECOATING

MODIFICATION CHARGESTATE

( SEE “VACUUM”)

EMBRITTLEMENT

(SEE “ATOX”)

(SEE“RADIATIONS”)


TEC/QMC 32


Nov 1995


TEC/QMC 33


FEP/VDA Pristine

VDA layer at BOL

14 days aged at 200 °C 44.9 days aged at 200 °C TC –100 °C/+100 °C


TEC/QMC 34


FEP/VDA 14 days at 200C


TEC/QMC 35


FEP/VDA 6400 cycles between –100/+100


TEC/QMC 36



TEC/QMC 37



TEC/QMC 38


ATOMICOXYGEN(ATOX)

OXIDATION

OXIDE LAYER

BREAKAGE

EROSION

PROTECTION

CONTAMINATIONCLOUD

GENERATION OFPARTICLES

DEGRADATIONMECHANICALPROPERTIES

CHANGE INTHERMO-OPTICAL

PROPERTIES

MASS LOSS

TEXTURE CHANGE

ELIMINATION OFCONTAMINANTS

PROPERTYRECOVERY

RUPTURE/DEFORMATION


Space Environment Effects : Atomic Oxygen


TEC/QMC 39


Neutral Composition during Medium Solar Activity

1

100

104

106

108

1010

1012

1014

1016

1018

1020

200 400 600 800 1000

N /m3

km

Ar

02

N2

N

OHeH


TEC/QMC 40


O- density

108

1010

1012

1014

1016

1018

1020

200 400 600 800 1000

O (N/m3)

km

High Solar Activity

Medium Solar Activity

Low Solar Activity


TEC/QMC 41


ATOMICOXYGEN(ATOX)

OXIDATION

OXIDE LAYER

BREAKAGE

EROSION

PROTECTION

CONTAMINATIONCLOUD

GENERATION OFPARTICLES

DEGRADATIONMECHANICALPROPERTIES

CHANGE INTHERMO-OPTICAL

PROPERTIES

MASS LOSS

TEXTURE CHANGE

ELIMINATION OFCONTAMINANTS

PROPERTYRECOVERY

RUPTURE/DEFORMATION


Space Environment Effects : Atomic Oxygen


TEC/QMC 42


Silver interconnector flown on Eureca. The silver is oxidised. Silver loss: 1 micron per 1021

atoms


TEC/QMC 43



TEC/QMC 44


HIGHVELOCITYPARTICLE IMPACT CRATERING

THROUGHHOLE

CHANGE INTHERMOOPTICAL

PROPERTIES

CONDUCTIVEPATH

LOSS OFMATERIAL

INTEGRITY/CRACK

INITIATION

EXPOSURE OFUNDERLAYER

NUMEROUS PROBLEMSPARTICULARLY

EMBRITTLEMENT/LEAK

ELECTRICALPROBLEMS

DEBRISCONTAMINATION

CLOUD

( SEE “ATOX”)


Space Environment Effects : Micrometeoroids & Debris


TEC/QMC 45



TEC/QMC 46


Cumulative number of impacts in ISS Orbit

10-12

10-10

10-8

10-6

10-4

0.01

1

100

10000

0.0001 0.001 0.01 0.1 1 10

N debrisN meteoroidsN total

Number m-2 year-1

Diameter (cm)

h = 400 km, inclination = 51.6o,year 2000


TEC/QMC 47


Cumulative number of impacts in Polar Orbit

10-12

10-10

10-8

10-6

10-4

0.01

1

100

10000

0.0001 0.001 0.01 0.1 1 10

N debris

N meteoroids

N total

Number m-2 year-1

Diameter (cm)

h = 800 km, inclination i = 98o


TEC/QMC 48


Cumulative number of impacts in GEO

10-10

10-8

10-6

0.0001

0.01

1

100

104

0.0001 0.001 0.01 0.1 1 10

N debrisN meteoroidsN total

Diameter(cm)

Number m-2 year-1

h = 35786 km, inclination i= 0.5o


TEC/QMC 49


HIGHVELOCITYPARTICLE IMPACT CRATERING

THROUGHHOLE

CHANGE INTHERMOOPTICAL

PROPERTIES

CONDUCTIVEPATH

LOSS OFMATERIAL

INTEGRITY/CRACK

INITIATION

EXPOSURE OFUNDERLAYER


EMBRITTLEMENT/LEAK

ELECTRICALPROBLEMS

DEBRISCONTAMINATION

CLOUD

( SEE “ATOX”)


Space Environment Effects : Micrometeoroids & Debris


TEC/QMC 50



TEC/QMC 51



TEC/QMC 52



TEC/QMC 53



TEC/QMC 54



TEC/QMC 55



TEC/QMC 56


Space Environment Effects : Re-entry

RUPTURE

LOSSMECHANICALRESISTANCE

ULTRA-HIGHTEMPERATURE

RE-ENTRYDYNAMICPRESSURE

PLASMA CHEMICAL REACTIONS

EROSION/CORROSION

SURFACE TEXTURECHANGES

LOSS OF MATERIALINTEGRITY

MODIFICATION OFHEAT EXCHANGES


EMBRITTLEMENT

THERMALPROBLEMS


TEC/QMC 57


Inflatable Re-entry Vehicle

Ablative shield

1st inflatable deceleration unit

2nd inflatable deceleration unit

IRDT


TEC/QMC 58


Re-entry Apollo 8


TEC/QMC 59


NUMEROUS PROBLEMS PARTICULARLY

INSULATION/ GASKETING

DEGRADATION OF MATERIAL FUNCTION

OFFGASSING/AGEING/CORROSION

COMBUSTION

BIOLOGICAL GROWTH

SMELL

LIFE SUPPORTING ATMOSPHERE

TOXIC GASES

LOSS OF MATERIAL FUNCTION

TOXINES

AGRESSIONS TO LIFE

CATASTROPHIC FAILURES

DISEASES

DISCOMFORT

Space Environment Effects : Manned Volumes


TEC/QMC 60


Conclusions

• During the whole lifetime of a spacecraft, materials are subjected to a large number of different environments, some of which can be very harsh and harmful to the integrity or functionality.

• Earth and space environment experienced by a spacecraft must both be considered during the design process.

• Material selection has to be biased towards the specific needs of space programmes. The environmental factors associated with space have a direct influence on material selection. The application dictates the use of a particular material type.

• Interactions between a material and the different environments to which it is exposed are quite often synergistic and not simply additive; i.e. the sum of both interactions is larger than each of the effects separately.


TEC/QMC 61


•Materials require evaluation to ensure adequate performance under a variety of combined conditions.

•Tests must be optimised –differentiate between primary and secondary parameters/degradation mechanisms.

•Simulation of these combined environments–Technical limitations–Cost effectiveness/ affordability

Conclusions (cont.)

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02 Interaction Materials Environments