Space Environment

Professional Development Short Course On:
The Space Environment
Implications for Spacecraft Design

Instructor:

Dr. Alan C. Tribble

http://www.ATIcourses.com/schedule.htm
ATI Course Schedule:
ATI's Space Based Radar: http://www.aticourses.com/space_environment.htm
Copywrite Alan C. Tribble

The Space Environment –

Summary
Adverse interactions between the space environment
and an orbiting spacecraft may lead to a degradation of
spacecraft subsystem performance and possibly even loss
of the spacecraft itself. This course presents an
introduction to the space environment and its effect on
spacecraft. Emphasis is placed on problem solving
techniques and design guidelines that will provide the
student with an understanding of how space environment
effects may be minimized through proactive spacecraft
design.
Each student will receive a copy of the course text, a
complete set of course notes, including copies of all
viewgraphs used in the presentation, and a
comprehensive bibliography.

Instructor
Dr. Alan C. Tribble has provided space environments effects
analysis to more than one dozen NASA, DoD, and commercial
February 2-3, 2009
programs, including the International Space
Beltsville, Maryland
Station, the Global Positioning System (GPS)
satellites, and several surveillance spacecraft.
$1095
He holds a Ph.D. in Physics from the (8:30am - 4:00pm)
University of Iowa and has been twice a
quot;Register 3 or More & Receive $10000 each
Principal Investigator for the NASA Space
Off The Course Tuition.quot;
Environments and Effects Program. He is the
author of four books, including the course text:
The Space Environment - Implications for Space Design, and
Course Outline
over 20 additional technical publications. He is an Associate
Fellow of the AIAA, a Senior Member of the IEEE, and was
1. Introduction. Spacecraft Subsystem Design, Orbital
previously an Associate Editor of the Journal of Spacecraft
Mechanics, The Solar-Planetary Relationship, Space
and Rockets. Dr. Tribble recently won the 2008 AIAA James A.
Weather.
Van Allen Space Environments Award. He has taught a variety
of classes at the University of Southern California, California 2. The Vacuum Environment. Basic Description –
State University Long Beach, the University of Iowa, and has Pressure vs. Altitude, Solar UV Radiation.
been teaching courses on space environments and effects
3. Vacuum Environment Effects. Solar UV
since 1992.
Degradation, Molecular Contamination, Particulate
Contamination.
4. The Neutral Environment. Basic Atmospheric
Who Should Attend: Physics, Elementary Kinetic Theory, Hydrostatic
Engineers who need to know how to design systems with
Equilibrium, Neutral Atmospheric Models.
adequate performance margins, program managers who
5. Neutral Environment Effects. Aerodynamic Drag,
oversee spacecraft survivability tasks, and scientists who
need to understand how environmental interactions can affect Sputtering, Atomic Oxygen Attack, Spacecraft Glow.
instrument performance.
6. The Plasma Environment. Basic Plasma Physics -
Single Particle Motion, Debye Shielding, Plasma
Oscillations.
Review of the Course Text:
7. Plasma Environment Effects. Spacecraft
“There is, to my knowledge, no other book that provides its
Charging, Arc Discharging.
intended readership with an comprehensive and authoritative,
yet compact and accessible, coverage of the subject of 8. The Radiation Environment. Basic Radiation
spacecraft environmental engineering.” – James A. Van Allen, Physics, Stopping Charged Particles, Stopping Energetic
Regent Distinguished Professor, University of Iowa. Photons, Stopping Neutrons.
9. Radiation in Space. Trapped Radiation Belts, Solar
Proton Events, Galactic Cosmic Rays, Hostile
Environments.
“I got exactly what I wanted from this
10. Radiation Environment Effects. Total Dose
course – an overview of the spacecraft
Effects - Solar Cell Degradation, Electronics Degradation;
environment. The charts outlining the
Single Event Effects - Upset, Latchup, Burnout; Dose Rate
interactions and synergism were excellent. Effects.
The list of references is extensive and 11. The Micrometeoroid and Orbital Debris
will be consulted often.” Environment. Hypervelocity Impact Physics,
Micrometeoroids, Orbital Debris.
“Broad experience over many design 12. Additional Topics. Design Examples - The Long
teams allowed for excellent examples of Duration Exposure Facility; Effects on Humans; Models
applications of this information.” and Tools; Available Internet Resources.

Register online at www.ATIcourses.com or call ATI at 888.501.2100 or 410.956.8805 Vol. 96 – 17

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COURSE OUTLINE
• Plasma
• Introduction
– Environment
– Why Study SEE?
– Effects
– The Earth’s Environment
• Spacecraft Charging
– The Solar Environment
• Arc Discharging
• Vacuum • Radiation
– Environment – Environment
– Effects – Effects
• Solar UV Degradation • Total Dose
• Dose Rate
• Molecular Contamination
• Single Event
• Particulate Contamination
• Micrometeoroid/Orbital Debris
• Contamination Control
– Environment
• Neutral
– Effects
– Environment
• Hypervelocity Impact Damage
– Effects
• Effects on Humans
• Aerodynamic Drag
• Conclusions
• Sputtering
• Atomic Oxygen Erosion
• Spacecraft Glow

Sampler
Copyright Dr. Alan Tribble.
Applied Technology
2009
Do Not Reproduce Without Permission.
Institute (ATI)
Slide #2
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ABOUT THE INSTRUCTOR
• Dr. Alan Tribble
– Over Twenty Years Experience in Space Environments and
Effects
• Author of First Text on Space Environments & Effects
• Principal Investigator for the NASA Space Environments & Effects
Program
• Associate Editor for the AIAA Journal of Spacecraft and Rockets
• Instructor for Space Environments & Effects Courses Since 1992

– Winner of the 2008 AIAA James A. Van Allen Award
• Presented to recognize outstanding contributions to space and
planetary environment knowledge and interactions as applied to
the advancement of aeronautics and astronautics.

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MOLECULAR CONTAMINATION

• Molecular Films On the Order of 1 m Thick
May Be Deposited During On Orbit
Operations

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MOLECULAR REQUIREMENTS

Affected Operational If Single If 5 Optical
Element Parameter Criteria Surface Surfaces

~ 0.05 m ~ 0.004 m
UV Sensora Signal Strength < 10% Absorption
(0.2 - 0.3 m) (Level B) (~ Level A/20)

~ 0.015 ma
Solar Arraysb Power Production < 2% Power Loss N/A
(Level A)

s/ Ratio s < 2.0 initial s ~ 0.2 m
Thermal Control Surfaces N/A
(Initial OSR s = 0.06) (Level H)

~ 0.2 m ~ 0.04 m
Visible Sensor Signal Strength < 10% Absorption
(0.35 - 0.90 m) (Level H) (Level D)

~ 1.5 m ~ 0.3 m
IR Sensorc Signal Strength < 10% Absorption
(1.0 - 2.0 m) (>> Level J) (~ Level J)

a
assumes nominal contaminant absorptance profile - highly absorptive in the UV
b
assumes darker, photochemically deposited contaminant absorptance profile
c
requires cryogenic surfaces that retain contaminants

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Slide #5
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PARTICULATE CONTAMINATION

• Particulates on the Order of 1 m in Size May
Be Deposited During Manufacturing,
Assembly, Test, or Launch

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PARTICULATE REQUIREMENTS

Element Operational Required
Affected Parameter Criteria Cleanliness
IR Sensor Signal to Noise Ratio SNR > 8.0 200

s ~ 0.05
Thermal Control Absorption 350
 ~ 0.05
Surfaces Emittance 450
 ~ 1.0 650

Solar Arrays Power Production < 1% Power Loss 520

These Values Should Be Used For Comparison Only

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Slide #7
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THE ROCKET EQUATION - 1

• An Object of Dry Mass M, Moving With Velocity v,
Can Change Its Velocity by Ejecting a Mass of Fuel
m at velocity v'.
v v + v
v'
M+m M

m

INITIAL FINAL

• From Conservation of Momentum

( M  m)v  M (v  v)  mv  v'
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PHYSICAL SPUTTERING
• Due to the Large Impact Speed of the Neutrals
Some Surface Molecules May Be Dislodged Upon
Impact
• The Reaction is Highly Dependent Upon Impact
Energy and Surface Material Properties

IMPACTING
NEUTRAL

REFLECTED
NEUTRAL

SPUTTERED
MOLECULE

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AO MASS LOSS

• Mass Loss is Quantified by the Relation

dm  t REnvo dAdt
• The Erosion Rate is Given by

dx
 REnvo
dt
• Where RE is the Experimentally Determined
Reaction Efficiency

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SHUTTLE GLOW AND AURORA

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THE LEO PLASMA ENVIRONMENT

Parameter Value
1 x 1011 m-3
Plasma Density
Plasma Temperature 1000 K (0.13 eV)

Debye Length 1 cm
Electron Gyroradius 1 cm
Ion Gyroradius 3m

Electron Thermal Speed 200 km/s
Orbital Velocity 8 km/s
Ion Thermal Speed 1 km/s

Electron Plasma Frequency 2.8 MHz
Ion Plasma Frequency 16.6 kHz

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LEO GROUNDING RESULTS

ELECTRON
COLLECTION

PLASMA
POTENTIAL
ION
COLLECTION

NEGATIVE POSITIVE FLOATING
GROUND GROUND GROUND

STRUCTURES STRUCTURES STRUCTURES
~ 90% OF ARRAY A FEW VOLTS A FEW VOLTS
VOLTAGE POSITIVE NEGATIVE
NEGATIVE

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NOMINAL GEO CONDITIONS

Parameter Value
1 x 106 m-3
Plasma Density
Plasma Temperature 1,000,000 K (130 eV)

Debye Length 2m
Electron Gyroradius 7.5 km
Ion Gyroradius 3m

Electron Thermal Speed 6,000 km/s
Ion Thermal Speed 30 km/s
Orbital Velocity 3 km/s

Electron Plasma Frequency 900 Hz
Ion Plasma Frequency 50 Hz

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GEOMAGNETIC STORMS
SEVERE SPACECRAFT CHARGING
MIDNIGHT - 6 AM

ENERGETIC
Magnetopause
ELECTRONS
Compressed to < 10 RE
VIEW v
B
FROM x

TOP
ENERGETIC
PROTONS

Earth’s
Magnetic
HOT PLASMA
Solar
Field
PUSHED EARTHWARD
Wind
Lines
Compressed

Sun’s Earth’s
Magnetic Magnetic
Field Field
Dominant Dominant

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ESD ON SOLAR ARRAYS

Solar Arrays That Are Placed in Plasma
Chambers Are Observed to Arc.
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DIELECTRIC BREAKDOWN DAMAGE

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WHAT IS RADIATION?

• As an Energetic Particle Passes Through
Matter it Will Create Atomic Displacements
and/or Ionize Atoms in the Material
• As a Result the Material Properties Will be
Altered
• Radiation Can be Thought of as Anything
That Deposits Energy in a Material
– Charged Particles (Electrons, Protons)
– Uncharged Particles (Neutrons)
– Photons (Gamma Rays, X-Rays)

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FUNDAMENTAL FORCES

• Four Forces Electrical Force Always
– Strong Nuclear Dominates Outside
the Nucleus
• Important Near the
Nucleus
– Weak Nuclear
• Important Near the
Nucleus
– Electrical
• Very Significant for
Particles That are
Charged
– Gravitational
• Only Important for Very
Large Masses Nuclear Forces Only
Dominates Near the
Nucleus
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STOPPING POWER

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PHOTON CROSS SECTION

0 .2
Compton
0 .1 8
Pair Production
0 .1 6
Absorption Coefficient (cm^2/g)

Photoelectric
0 .1 4

Total
0 .1 2
Cross
Section 0 .1
(cm2/g)
0 .0 8

0 .0 6

0 .0 4

0 .0 2

0
0 -1 100 101 102
10.1 1 10 100
Photon Energy (MeV)

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ATMOSPHERIC NEUTRONS

• The Neutron Flux is Neutron Flux vs Altitude

a Function of Altitude 1.4
1.2

Flux (n / cm^2 s)
and Latitude 1
0.8
0.6

• The Worst Location 0.4
0.2

is a Polar Route at 0
0 20 40 60 80 100
Altitude (Thousand Feet)
About 55,000 Feet
Neutron Flux vs Latitude

1.6
1.4

Flux (n / cm^2 s)
1.2
1
0.8
0.6
0.4
0.2
0
Normand, E., and Baker, T. J., “Altitude and Latitude Variations in
0 20 40 60 80 100
Avionics SEU and Atmospheric Neutron Flux,” IEEE Tns. Nuc.
Latitude (Deg.)
Sci., Vol. 40, No. 6, pp. 1484 - 1490, December 1993.

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RADIATION IN SPACE

• Trapped Radiation Belts (Van Allen Belts)
– Energetic Electrons and Protons That Are Trapped by the
Earth’s Magnetic Field
• Solar Particle Events (SPE’s)
– Energetic Particles, Mostly Protons, Emitted During Solar
Flares
• Galactic Cosmic Rays (GCR’s)
– Energetic Nuclei Originating Outside the Solar System
• Hostile Radiation Environments
– Nuclear Weapons in Space
• Nuclear Power Systems
– Radioisotope Thermoelectric Generators (RTG’s)

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VAN ALLEN BELTS

Displaying a Model of the Explorer 1 Spacecraft are (l-r):
Dr. James Pickering (JPL), Dr. James Van Allen (Univ. of Iowa), and Dr. Wehrner Von Braun (MSFC).

Van Allen Published the First Data on the Trapped Radiation Belts,
Which are Sometimes Called the Van Allen Belts.
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INTENSITY OF THE BELTS

OMNIDIRECTIONAL EQUATORIAL Flux
Omnidirectional Equatorial FLUX

109
1.0 0 E+ 0 9
ELECTRONS PROTONS
8
10
1.0 0 E+ 0 8
0.1.1 MeV
0 MeV
107
1.0 0 E+ 0 7
Flux (per sq cm per s)

1.0 0 E+ 6 6
10 0
0 .1 MeV
0.1 MeV
Flux1.0 0 E+ 5 5
10 0
-2 -1
(cm s )
1.0 0 E+ 4 4
10 0
1 MeV
1 MeV
1.0 0 E+ 3 3
10 0 10 MeV
1 MeV
1 MeV
1.0 0 E+ 2 2
10 0
1 0 MeV
1.0 0 E+ 1 1
10 0
3 MeV
3 MeV
1.0 0 E+ 0 0
10 0
10 8 6 4 2 2 4 6 8 10
-1 0 -8 -6 -4 -2 0 2 10
Earth Radii
Earth Radii

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SPE COMPOSITION

Large Solar Proton Event Spectra at 1 AU
Feb 1956
Integral Fluence, (protons /

1.00E+11
Nov 1960
Aug 1972
1.00E+10 Aug 1989
Sep 1989
cm^2)

1.00E+09 Oct 1989

1.00E+08

1.00E+07
1 10 100 1000
Kinetic Energy (MeV)

Wilson, J. W., Cucinotta, F. A., Simonsen, L. C., Shinn, J. L., Thibeault, S. A., and Kim, M. Y.,
quot;Galactic and Cosmic Ray Shielding in Deep Spacequot;, NASA TP 3682, December 1997

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GCR COMPOSITION

Galactic Cosmic Ray Fluence, Solar Max (1981)

Z=1
1.00E+06 Z=2
1.00E+05
Annual Fluence, (particles / cm^2 - A MeV)

Z: 3 - 10
Z: 11 - 20
1.00E+04
Z: 21 - 28
1.00E+03
1.00E+02
1.00E+01
1.00E+00
1.00E-01
1.00E-02
1.00E-03
1.00E-04
1.00E-05
1.00E-06
1.00E-01 1.00E+00 1.00E+01 1.00E+02 1.00E+03 1.00E+04 1.00E+05 1.00E+06
Kinetic Energy (A MeV)

Wilson, J. W., Cucinotta, F. A., Simonsen, L. C., Shinn, J. L., Thibeault, S. A., and Kim, M. Y.,
quot;Galactic and Cosmic Ray Shielding in Deep Spacequot;, NASA TP 3682, December 1997

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RADIATION DAMAGE THRESHOLDS

• In Many Materials, the Total Dose of
Radiation is the Critical Issue in Determining
Useful Lifetime

Material Damage Threshold (RAD)
101 - 102
Biological Matter
102 - 104
Electronics
105 - 107
Lubricants, Hydraulic Fluid
106 - 108
Ceramics, Glasses
107 - 109
Polymeric Materials
109 - 1011
Structural Metals

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GPS RADIATION ENVIRONMENT

GPS Tra20,000 km @ 55 degrees - 55 De g
ppe d Ra dia tion: 20,000 km

10 1
1.00E+01
Electrons - Solar Max.

Protons
10 0
1.00E+00
Energy (MeV)

Energy
(MeV) Protons
Electrons - Solar Min.
Electrons - Solar Min
10 -1
1.00E-01
Electrons - Solar Max

1.00E-02
10 -2
1.00E+04 1.00E+05 1.00E+06 1.00E+07 1.00E+08 1.00E+09 1.00E+10 1.00E+11 1.00E+12 1.00E+13
10 4 10 5 10 6 10 7 10 8 10 9 10 10 10 11 10 12 10 13
Flue nce (# cm ^-2 day^-1)
Fluence (cm -2 day -1)

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GPS RADIATION DOSE

Altitude = 20,000 km
Inclination = 55 deg.
Shielding = Full-Sphere
10000.00

To ta l

1000.00 Pro to n

Ele c tro n

Bre m s.
100.00
Dose (rad/day)

10.00

1.00

0.10
10 100 1000
Shie ld ing T kne ss (m ils - Al)
hic

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DESIGN EXAMPLE: SOLAR ARRAY SIZING

• Solar Array Size is Driven by the Amount of Energy
That Must be Produced
– A = Solar Array Area (m2)
– P = Power Required (W)
P
–  = Efficiency A
S
• Efficiency is Degraded by Radiation
– BOL Value is Greater Than the EOL Value
• Efficiency Loss is Minimized by Adding a Transparent Shield
– Coverslide
– S = Sun’s Power Output (1367 W/m2 at Earth Orbit)

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SEE ILLUSTRATION

Radiation
(proton, ion, neutron, …)
VIN
Gate
VDD VSS
VOUT
Source Drain Source

p+ n+ n+ p+ p+ n+
n-well
Upset occurs if
channel current turned on

p-type substrate
Latchup occurs if
parasitic current loop initiated

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MITIGATION TECHNIQUES

• Shielding
– Prevent the Radiation Environment From Reaching the Crew
or Sensitive Electronics
• Not Effective on Very Energetic (GeV) Charged Particles
• Parts Selection
– Choose Parts or Materials That Can Withstand the Total
Dose Environment Anticipated
– Choose Parts That are Immune or Resistant to SEE
• Fault Tolerance
– Hardware
• Redundancy, Majority Voting, …
– Software
• Error Detection and Correction (EDAC), Hamming Codes, …

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MEDIUM IMPACT CRATER

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COLUMBIA ACCIDENT INVESTIGATION

• Executive Summary
– The Physical Cause of the Loss of Columbia and its Crew
Was a Breach in the Thermal Protection System on the
Leading Edge of the Left Wing, Caused by a Piece of
Insulating Foam Which Separated From the Left Bipod
Ramp Section of the External Tank at 81.7 Seconds After
Launch, and Struck the Wing in the Vicinity of the Lower Half
of Reinforced Carbon-Carbon Panel Number 8. During Re-
Entry This Breach in the Thermal Protection System Allowed
Superheated Air to Penetrate Through the Leading Edge
Insulation and Progressively Melt the Aluminum Structure of
the Left Wing, Resulting in a Weakening of the Structure
Until Increasing Aerodynamic Forces Caused Loss of
Control, Failure of the Wing, and Breakup of the Orbiter.
This Breakup Occurred in a Flight Regime in Which, Given
the Current Design of the Orbiter, There was no Possibility
for the Crew to Survive.
• Columbia Accident Investigation Board, August 2003

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METEOR SHOWERS
• Meteor Showers
• Most MM’s Originate From
Comets or Asteroids – Quantrantids
• January 1 - 6
• Meteor 'Showers' Are Those
– Lyrids
Few Days of the Year When • April 19 - 24
Ground Observers May See – Eta Aquarids
a >10 Fold Increase in MM • May 2 - 7
Flux for a Period of a Few – Delta Aquarids
Days. • July 15 - August 15
– Perseids
• With the Exception of Very
• July 27 - August 17
Short Term Missions, i.e.,
– Orionids
The Shuttle Orbiter, These • October 12 - 16
Short Term Variations Will – Taurids
Not be Significant. • October 26 - November 25
• The Data That Follows is – Leonids
• November 15 - 19
Based on a Yearly Average
– Geminids
for the Micrometeorite Flux.
• December 7 - 15

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CUMULATIVE EFFECTS

• 5 Years Exposure in
LEO Resulted in
Noticeable Surface
Damage to Many
Panels on the Long
Duration Exposure
Facility (LDEF)

Sampler
Applied Technology
2009
Institute (ATI)
Slide #37
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ED WHITE’S 1965 SPACE WALK

Ed White’s Space Walk in 1965 Generated Some Orbital Debris When a
Glove Floated Out of the Open Hatch of the Capsule
Sampler
Applied Technology
2009
Institute (ATI)
Slide #38
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SHIELDING

• Whipple Shield
– Outer Layers Fragment Impacting Particle
– Inner Layers Catch Fragments

Sampler
Applied Technology
2009
Institute (ATI)
Slide #39
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NASA INTERNET SITES

• Glenn Research Center • Jet Propulsion Laboratory
– Space Environments and – Radiation Effects Group
Experiments Branch • http://parts.jpl.nasa.gov
• http://www.grc.nasa.gov/WWW • Johnson Space Center
/epbranch/
– Orbital Debris Program Office
• Goddard Space Flight Center • http://orbitaldebris.jsc.nasa.gov
– Radiation Effects and Analysis
• Langley Research Center
• http://radhome.gsfc.nasa.gov
– Space Environments and
– National Space Science Data
Technology Archive System
Center (NSSDC)
(SETAS)
• http://nssdc.gsfc.nasa.gov
• http://setas-www.larc.nasa.gov/
– Community Coordinated
• Marshall Space Flight Center
Modeling Center (CCMC)
– Space Environments and Effects
• http://ccmc.gsfc.nasa.gov/mod
Program
elweb/
• http://see.msfc.nasa.gov

Sampler
Applied Technology
2009
Institute (ATI)
Slide #40
www.atribble.com
www.aticourses.com

OTHER INTERNET SITES
• NOAA • Space Environment Information
System (SPENVIS)
– Space Weather Prediction
Center – interface to models of the space
environment and its effects,
• http://www.swpc.noaa.gov
including the natural radiation
• Space Weather
belts, solar energetic particles,
– Science News and Information cosmic rays, plasmas, gases,
• http://www.spaceweather.com and quot;micro-particlesquot;.
– Space Science Institute • www.spenvis.oma.be
• http://www.spaceweathercente
r.org/
• Instructor’s Web Site
– Links to Site’s of Interest
• http://www.atribble.com

Sampler
Applied Technology
2009
Institute (ATI)
Slide #41
www.atribble.com
www.aticourses.com

SPACE ENVIRONMENT EFFECTS

Space Environments and Effects
VACUUM NEUTRAL RADIATION
PLASMA MMOD
Atomic
Outgassing/ Aerodynamic Spacecraft Van Allen Galactic Solar Proton
Solar UV Sputtering Oxygen Spacecraft Charging Impacts
Contamination Drag Glow Belts Cosmic Rays Events
Attack

Total Dose Degradation; EMI Due To
EMI From Arc Discharging
Avionics
Single Event Effects Impacts

Noise
Degradation of Sensor
Degradation of Torques Due to Induced
Attitude Determination &
Induced Torques Source for
Coatings
Sensors Potentials
Control
Spacecraft Subsystems

Sensors
Destruction/
Reduction in Coverslide Reduction in Coverslide
Degradation of Solar Cell Output
Arcing on Solar Arrays Obscuration of
Electrical Power
Transmittance Transmittance
Solar Cells

Total Dose Degradation; Penetration of
Environmental Control & Life
Toxic Fumes EMI From Arc Discharging
Single Event Effects Habitat
Support

Drag Makeup
Rupture of
Fuel
Propulsion
Pressurized Tanks
Requirement
Dielectric Breakdown on
Penetration
Structures
Surfaces
Total Dose Degradation;
Degradation of
Telemetry, Tracking, and
EMI From Arc Discharging EMI due to impacts
Single Event Effects
Sensors
Communications
Change in
Change in Absorptance / Change in Absorptance /
Cold Surfaces May Experience Heating Absorptance /
Thermal Control
Emittance Emittance
Emittance

Sampler
Applied Technology
2009
Institute (ATI)
Slide #42
www.atribble.com
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SYNERGISTIC EFFECTS
VACUUM NEUTRAL PLASMA RADIATION MMOD
Ato m ic G a la c tic
O u tg a ssin g / Ae ro d yn a m ic Sp a c e c ra ft Sp a c e c ra ft Va n Alle n So la r Pro to n
So la r UV Sp u tte rin g O xyg e n C o sm ic Im p a c ts
C o n ta m in a tio n Dra g G lo w C h a rg in g Be lts Eve n ts
Atta c k Ra ys

Ph o to c h e m ic a l So la r C yc le
Ph o to e m issio n o f
So la r C yc le A lte rs A tm o sp h e ric De n sity
So la r UV De p o sitio n o f A lte rs O D
VACUUM

Ele c tro n s
C o n ta m in a n ts De n sity

O u tg a sse d O u tg a sse d
O u tg a ssin g /
Ma te ria l Ma y Ma te ria l Ma y
C o n ta m in a tio n
En h a n c e G lo w In c re a se Arc Ra te

Ma y Re fle c t Re m o ve s O D
Ae ro d yn a m ic
C o n ta m in a n ts to Fro m Lo w e r
Dra g
S/ C O rb its
Sp u tte re d Ma te ria l
Ma y b e
NEUTRAL

Sp u tte rin g
C o n ta m in a n t
So u rc e
A O Re sista n t
AO Ma y C le a n AO Atta c k Ma y
Ato m ic O xyg e n Ma te ria ls a re
C o n ta m in a te d Alte r Su rfa c e
Atta c k Su sc e p tib le to
Su rfa c e s C o n d u c tivitie s
G lo w
Sp a c e c ra ft
G lo w
PLASMA

C h a rg in g
Charging May
Sp a c e c ra ft Ma y
Enhance
C h a rg in g En h a n c e
Contaminantion Rate
Sp u tte rin g

Va n Alle n Be lts
RADIATION

G a la c tic Ra d ia tio n Ma y
Ra d ia tio n Ma y
C o sm ic Ra ys Stim u la te
In c re a se C h a rg in g
O u tg a ssin g SPE's
So la r Pro to n
Su p p re ss
Eve n ts
G C R's
Im p a c ts Ma y
MMOD

Im p a c ts Ma y Im p a c ts Ma y Exp o se Im p a c t
Im p a c ts G e n e ra te Slig h tly Un d e rlyin g Va p o riza tio n Ma y
C o n ta m in a n ts In c re a se Dra g Su rfa c e s to Stim u la te Arc in g
Ero sio n

Sampler
Applied Technology
2009
Institute (ATI)
Slide #43
www.atribble.com
www.aticourses.com

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