NASA Goddard Space Flight Center’s
Cryogenics and Fluids Branch
Code 552
by
Eric A. Silk, M.S., Ph.D.
NASA Goddard Space Flight Center, Greenbelt, MD., 20771
Presented to
Goddard Contractor’s Association
NASA Goddard Spaceflight Center
Greenbelt, MD., 20771
September 8, 2016
Outline
• What is Cryogenics?
• History of the Branch
• Branch Personnel
• Lines of Business
• Technology Development Efforts
• Community Involvement/Outreach
• Conclusions
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September 8, 2016 Greenbelt, MD., 20771, USA
What is Cryogenics?
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What is Cryogenics?
Cryogenics is the art
and/or science of
making things cold. The
NBS (National Bureau
of Standards) defines
cryogenic temperatures
as beginning at 123K.
Superconducting Magnets
YBCO cubic magnet over BSSCO
disc magnet in LN2
Key Notes:
 Fundamental physics based phenomena can change at low
temperatures (i.e., cryogenic temperatures).
 Cryogenic payloads are becoming commonplace on NASA missions
 Cryogenics vs. Cryonics
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Fundamental Cryogens
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Cryogenic Materials
Cryogenic engineering deals with the
practical application of very lowtemperature process and techniques.

The development of such processes
and techniques often are in realm of
low-temperature physics.
Saturation Temperatures of Common
Cryo-fluids at 1 atm
3He
4He
H2
Ne
N2
6
3.2 K
4.2 K
20.4 K
27.1 K
77.3 K
CO
Ar
O2
CH4
Kr
81.7 K
87.3 K
90.2 K
111.6 K
120.0 K
NASA Goddard Contractors Association
September 8, 2016 Greenbelt, MD., 20771, USA
Low Temperature Effects
Fundamental physics based phenomena can change at
low temperatures (i.e., cryogenic temperatures).
YBCO cubic magnet over BSSCO
disc magnet in LN2
 Thermal Conductivity
 Specific Heat (single vs. multiple values)
 Structural
 Elasticity (Thermal expansions and/or contractions)
 Stiffness and/or Ductility (embrittlement may be prevalent)
 Electrical phenomena
 Superconductivity
 Quantum Effects
 Superfluid Helium (i.e., He-II)
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Branch History
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Brief Chronology
 1980: Cryogenics, Fluids, and Propulsion Branch was created as
Code 713
 Cryogenics sections developed cryogenic cooling systems
 Propulsion section developed spacecraft propulsion systems
 Fluids section supported cryogenic and propulsion fluid analyses and
developed gas mixture systems
 1997: Engineering Directorate had reorganization and became
Code 500
 Cryogenic and Fluids Branch (Code 552) was established within the
Instrument Technology Center (now ISTD)
• Cryogenic and Fluids Branch focus on cryogenic cooling systems and gas
mixture systems
 Propulsion, Code 574—later Code 597—was established within the
Guidance, Navigation, and Control Center
• Most “Fluids” people transferred to Code 574
• Remaining fluids work is in support of cryogenic fluids
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Cryogenics & Fluids Facilities
Building 7 Basement Laboratory
Then
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Now
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Cryogenics & Fluids Facilities
 Area 400 (Hazardous Test Facility) retained by Cryogenics and Fluids
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What Does Code 552 Do?
Mission Proposals
- Design of Temperature
Control System Architectures
- Design, analysis and test of
cryogenic system components
- Technical expertise
 ADRs
- Cryogenic Systems
Engineering
 Cryocoolers
- Conceptual studies
Technical Reviews
- Spaceflight Programs (PDR,
CDR, etc.)
- SBIRs
- BAAs
- Strategic thrusts (e.g., NASA
Roadmap)
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Technology Development
 Cryo-fluid storage/transfer
systems
 Advanced Cryostats
- Consulting
- Product development and/or
leadership
- Structural and Thermal
analysis
- Design, development and
assembly
- Low – Mid TRL promotion
- Materials compatibility and
testing
- Technology proposal
development
- Training in proper handling
of cryogens
- Technology customization and
infusion
- Component fabrication
- External Code 552
technologies
- Nationwide Space Grant
Consortium submissions
 Optics
- IDL and MDL
 Radiators
- Journals (e.g., Elsevier
Journal of Applied Thermal
Engineering)
Engineering Support
 Mechanisms
- Purchasing and acquisitions
(e.g., cryocoolers)
- Technical oversight of
contracts
- On orbit analysis of cryosystems
 Heat Pipes/LHPs
 Superconducting Detectors
NASA Goddard Contractors Association
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Branch Personnel
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Technical Backgrounds
Degree Background
Degree Levels
Statistics
 30 Branch Members
 Mechanical
Engineering
 Ph.D. (11)
 26 Civil Servants
 Aerospace
Engineering
 Masters (6)
 Bachelors (7)
 4 Contractors
 Materials Science &
Engineering
 Low Temperature
Physics
 27 Full Time
Employees
 3 Co-ops
 Nuclear Physics
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Lines of Business
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Key Lines of Business
Cryogenic Temperature Control System
Magnetic
Refrigeration
Systems

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Mechanical
Cryocoolers
Cooling system
design,
fabrication,
assembly and
test

Cryocooler
integration
and testing


Cryocooler
SME
ADR & HTS
Leads SME


Contract
technical
support
Contract
technical
support
Cryogenic &
Microgravity Fluid
Management
Thermophysical
Properties
Testing

 Technical
Support
 SME for low
temperature
thermal
performance
of materials
 Cryogenic
testing


Dewar and fluid
system design,
assembly and
testing
Cryofluid SME
Contract
technical
support
NASA Goddard Contractors Association
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Sub-Kelvin Cooling
 Dilution Refrigeration using He3/He4 mixture (mK scale)
 Nuclear Demagnetization Refrigeration (µK scale)
 Adiabatic Demagnetization Refrigeration (mK scale)
Notes:
 Dilution refrigeration has been performed on spaceflight missions
in an open loop cycle.
 Adiabatic Demagnetization Refrigeration has been successfully
demonstrated in space on Astro-E2 and Astro-H.
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ADR Systems
Adiabatic Demagnetization Refrigeration relies upon magnetic
cooling of a paramagnetic material. Heat transfer is fostered
through the magneto-caloric affect.
1
Entropy [J/mol-K]
S1
δQ= T1(S1-S2)
H=H1
S3=S2
3
2
T2
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H0=0
Temperature [mK]
Step 1-2: Pre-cool via
coupling to cold sink
and apply a magnetic
field
Step 2-3: Isolate paramagnet from cold
sink, reduce magnetic
field to initial value
Step 3-1: System reconditions to initial value
T1
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ADR System Component
5 key components for each stage
 Paramagnetic material
 Superconducting magnet
 Heat switch
 Thermally isolating support
structure
 Thermometers
Ti 15-3-3-3; Shell 0.127 mm thick
Lateral suspension
Paramagnetic
Materials
Superconducting
Magnet
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HTS Leads
High Temperature Superconducting leads are used to provide current
to the ADR system internal to the cryogenic volume without
producing residual heating.
Note: In the superconducting state, electrical resistance
approximates to 0 Ohms.
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Goddard Flight Systems
Astor-E XRS
Astor-E2 XRS2
Astro-E XRS
Launch Date: 2000
Est. Lifetime: 2 years
Ne/He/ADR System
Astro-E2 XRS2
Launch Date: 2005
Est. Lifetime: 3 years
Ne/He/ADR System
Astro-H SXS
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Astro-H SXS
Launch Date: 2016
Est. Lifetime: 3 years
He/ADR System
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Cryogenic & µ-g Fluid Mgmt.
Traditionally, Cryogenic materials (in either solid or liquid phase)
have been used to foster cooling to desired cryogenic temperatures.
• Solid Cryogens
Argon (Triple Point Temperature = 83.8 K)
Nitrogen (Triple Point Temperature = 63.2 K)
Neon (Triple Point Temperature = 24.4 K)
Hydrogen (Triple Point Temperature = 14.0 K)
• Liquid Cryogens
4He (Lambda Point Temperature = 2.17 K)
3He (0.34 K)
Note: Cryomaterials provide cooling over temperature range
0.3 - 80 Kelvin with some gaps.
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Stored Cryogens
 Capable of operating with 300 K main shell
 Bulk cooling available
 Lifetime limited by heat input and mass/volume constraints
Dt = ml/Q
where Dt = lifetime, m = mass, l = heat of vaporization or
sublimation, and Q is the total heat input
 Substantial ground and launch pad operations
System is “active” any time it contains cryogens
Cryogen must be conditioned prior to launch to maximize
on-orbit lifetime
 Hazards associated with stored cryogens
Extreme cold
Asphyxiation
Overpressurization
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Stored Cryogen Missions
Mission
Cooler
Issues
Mission Outcome
NIMBUS 6/LRIR
1975
Solid NH3/CH4
Premature boiloff
Successful
HEAO-B
1978
Solid NH3/CH4
Premature boiloff
Successful
NIMBUS 7/LRIR
1978
Solid NH3/CH4
Premature boiloff
Successful
COBE
1989
SHe
None
SHOOT
1993
SHe, 1.1-3 K
Ice plugs in emergency vent line
NICMOS
1997
Solid Nitrogen
Distortion of dewar from expansion of SN2
WIRE
1999
Solid Hydrogen
Premature ejection of cover
XRS1/Astro-E1
2000
SHe/Solid Neon
None
Spitzer (SIRTF)
2003
SHe
Ice plug in vent line
XRS2/Astro-E2
2005
SHe/Solid
Ne/cryocooler
Ice plug and explosion of GSE helium
tank; contamination of dewar guard
vacuum with He gas on orbit
WISE
2009
Solid H2/H2
Premature boiloff
2016
Cryocooler/HeII/ADR
Astro-H/SXS
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Launch
Loss of spacecraft on orbit
Outrageous success!
Successful
Focus issues; short lifetime;
retrofitted w/ cryocooler
Loss of mission
Rocket failure
Recovered
Successful operation (2
weeks) until catastrophic
venting of He
Successful
Set new low temperature
record. Incomplete science
survery.
NASA Goddard Contractors Association
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Stored Cryogens
SHOOT: 1993 launch
Demonstrated cryogen
transfer between tanks
COBE: 1989 launch
Achieved 10 month lifetime
Helium Heat Load ≈ 70 mW
XRS: 2000 launch Neon Heat Load ≈100 mW
XRS2: 2005 launch Helium Heat Load ≈1 mW
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Robotic Refueling Mission 3
 Transfer of liquid
phase cryogen
from a source
dewar to a receiver
dewar
 No vent transfer
 No mechanical
pumping of
cryogen
 552 is Lead for
Cryogen Demonstration System
 ISS is µ-g platform
Ground System Cryogen Freeze Testing Using Argon
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Mechanical Coolers
Cryocoolers are mechanical coolers designed for cooling to
cryogenic temperatures.
 Cooling available over temperature range 4 - 100 K
Cryocooler designs are optimized to operate at a particular
temperature, and effectively cover a small range of
temperatures
Most cryocoolers in-orbit are single-stage coolers operating at
T > 55 K
Temperature lift for heat rejection
 Compressor operates at ~270 - 300 K
Planetary missions need 150 – 200 K compressor
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Types of Cryocoolers
System Type
Mechanical
Mechanical
Mechanical
Mechanical
AC
DC
Example
Joule-Thompson
Cycle
W
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Compressor
Heat Exchanger
Type
Regenerator
Regenerator
Recuperator
Recuperator
Cold End
Component
Displacer
Pulse Tube
Turbine
J-T Valve
ṁ
Recuperative
Heat
Exchanger
Note: Cryocoolers typically perform somewhere
between 3% and 8% of their Carnot efficiency.
Cooler Name
Stirling
Pulse Tube
Turbo-Brayton
J-T Cooler
J-T
Expansion
Valve
Heat
Exchanger
Q in
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Types of Cryocoolers
• Reverse Turbo-Brayton
– High speed rotary compressor and expander
– Recuperative heat exchanger
– Moving parts supported by gas bearings
• Stirling
–
–
–
–
Linear compressor with pneumatically driven displacer
Regenerative heat exchanger
Moving parts supported by flexure springs or gas bearings
Most cryocoolers on-orbit are Stirling cycle machines
• Pulse tube
– Linear compressor with tuned expansion pipe
– Regenerative heat exchanger
– No cold moving parts
• Joule-Thompson
– Isenthalpic expansion of gas through an orifice
– Sometimes used as low temperature stage for a Stirling or
pulse tube cooler
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Cryocooler Missions
Left: Sunpower M77
(RHESSI)
Above: Creare Reverse
Brayton (HST/NICMOS)
Above: NGST Pulse Tube
(MIRI JT Pre-cooler)
Right: Ball Stirling
(LDCM/TIRS)
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Operational Features
 Point cooling
Cooling at multiple locations requires thermal distribution system
(e.g., copper or aluminum straps, capillary pumped loop)
Multi-stage coolers can provide point cooling at different
temperatures
 Anticipated lifetime is 5 - 10 years
Electronics may be life-limiting component for many cryocoolers
“Low-cost cryocoolers” are expected to have lower reliability
 Vibration
Linear cryocoolers (Stirlings and pulse tube coolers) have residual
vibrations on the order of 1 N
– Can be reduced by an order of magnitude in the axial
direction using vibration cancellation algorithm in the drive
electronics
Rotary cryocoolers (Reverse Turbo-Brayton) have no measurable
vibration
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Thermophysical Properties Lab
 New laboratory brought online in summer 2016
 Two cryostats capable of temperature testing 4K – 300K
 Thermal Conductivity and Emissivity measurements
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Summary of Missions
Mission
Past
Present
Future
Magnetic
Refrigeration
Systems
Astro-E
Astro-E2
Astro-H
PIPER†
HIRMES†
Astro-H2?
PIXIE
SGG
Far IR Telescope
†Airborne
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Cryocoolers
RHESSI
HST/NICMOS
EOSAURA/HIRDLES,
GOES-RBI
TIRS-I
TIRS-II
WFIRST
WFIRST
PIXIE
SGG
Far IR Telescope
Cryogenic &
Thermophysical
Microgravity Fluid
Properties
Management
Measurements
NIMBUS 6, HEAO-B
NIMBUS 7, COBE,
SHOOT, NICMOS,
WIRE, Astro-E,
Spitzer, Astro-E2,
WISE, Astro-H
RRM3
Astro-H
OVIRS
Hybrid Plane
TiME
WFIRST
JWST
missions
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Technology Development Efforts
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SBIRs
Agency Subtopics Supported
 S1.09: Cryogenic Systems for Sensors and Detectors (Lead)
 H2.01: Cryogenic Fluid Management Technologies
(Participant)
 S3.07: Thermal Control Systems (Participant)
Present Awards
 Phase II: A High Efficiency 30-K Cryocooler with Low
Temperature Heat Sink, Creare
 Phase I: A Shielded 3-T HTS ADR Magnet Operating at 3040K, Superconducting Systems, Inc.
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A Low-G Ideal Integrating Bolometer (IIB)
PI: Ed Canavan/552
Description and Objectives: (Why) : We propose to
develop a novel detector to enable a new class of far-IR
spectroscopic surveys. Achievable sensitivity for these
devices is roughly 2 orders of magnitude better than current
devices. By reducing detection times by a factor of 10 000,
the IIB enables rapid surveys of cosmological volumes.
Key challenge(s)/Innovation: Circumvent limitations
on bolometer sensitivity through the use of:
• a phononic crystal, an array of holes optimized to
minimize phonon transmission, to obtain extremely low
conductance
• a micro-scale superconducting heat switch to control
heat flow
Approach: (How)
• In FY15 effort, fabricated micro-heat switch, and
successfully demonstrated switching of electrical
conductance; thermal conductance testing underway.
• Proposed effort will integrate the heat switch onto a
phononic crystal structure, currently in development under a
separate effort
Application / Mission: (Future Plans)
A background-limited high resolution far-infrared (0.3 – 3
THz) spectrometer, initially for balloon observatories,
eventually for the Far-IR Surveyor mission.
Collaborators:
A. Kogut/665, T. Stevenson/553, K. Denis/553
Canavan (GSFC/ 552) 09/11/2015
Micrograph of IIB pixel
Isolated
membrane
Completed test chip
Superconducting
heat switch
FTE and Procurement Allocation:
0.85 FTE / $30k procurement / $10k WYE
Top Level Milestones and Schedule:
Q1: Complete testing of micro heat switch;
complete design of new devices
Q2 – Q3: fabricate devices
Q4: complete device testing
Space Technology Roadmap Mapping:
8.1.1: Detectors and focal planes
Technology Readiness Level:
Starting TRL: 2; End TRL 3
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Cryogenic LH2+LO2 Propulsion for Planetary Science Mission
NASA/ GSFC, NASA/ MSFC
PI: Shuvo Mustafi
Contact: Shuvo Mustafi – [email protected] , 301-286-7436
Introduction
• Cryogenic Liquid Hydrogen (LH2) and Liquid Oxygen (LO2)
propellants provides the highest specific impulse for any
practical chemical propulsion system
• LH2+LO2 propulsion provides high ∆V and/or high dry mass
spacecraft with lower spacecraft wet mass.
• A detailed design study comparing LH2+LO2 propulsion with
conventional hypergolic propulsion using Mono Methyl
Hydrazine (MMH) and Nitrogen Tetra Oxide (NTO) was
performed by GSFC and MSFC on a representative mission to
Titan, the Titan Orbiter Polar Surveyor (TOPS).
•
•
•
8.5+ Years Cryogenic Propellant Storage Mission
Launch in 2022 – Jupiter is not available for a gravity assist.
∆V = 5887m/s; Non-Main Propulsion Dry Mass = 595.1 kg; Science Payload Mass = 53.3
kg; 7 Engine Burns
TOPS Design Study Results
• For the TOPS mission, passively cooled LH2+LO2 reduces launched
spacecraft mass by 43% and allows for launch on an Atlas launch
vehicle. The same mission cannot be performed using a MMH+NTO
propulsion and an Atlas launch vehicle.
• Subcooling cryogenic propellants on the launch pad enables multiyear storage of LH2 without adding launched mass. For the TOPS
Mission Subcooling saved LH2 boil-off mass that amounts to 56% of
science payload mass.
• Subcooling triples the in-space vent-free hold time of LH2 by just
processing the hydrogen on the ground.
• LH2+LO2 propulsion provides an enabling solution for many
missions that have high ∆V and/or high dry mass constraints, such
as missions to and from many planetary science destinations
including planets, moons, asteroids, comets.
• TOPS Mission and other planetary science missions can be
accomplished without any in-space active cooling.
LH2+LO2 Propulsion Required Technology
• Storage





High Performance Advance Multi-Layer Insulation
Low Conductivity Supports
Launchpad subcooling to enhance long duration in-space storage
Propellant Tank Pressure Control
Tank Liquid Acquisition Devices




Electric Pumps and Motors
Igniters
Injector and Chamber Design
Long-life Cryogenic Valves
• 890 N (200 lbf) LH2+LO2 Engine
Application / Mission:
• Science Missions to Outer Planets/Moons/ Asteroids
• In-Space Cryogenic Upper Stages and Depots
• Flexible architecture Human Missions
• Asteroid Missions, Martian Missions, Lunar Mission
• High Isp Advanced Electric Propulsion Missions
• Cryogenic Hydrogen Radiation Shielding
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Community
Involvement/Outreach
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September 8, 2016 Greenbelt, MD., 20771, USA
Outreach Activities








USA Science and Engineering Festival (2014)
NASA Goddard Science Jamboree (annually)
DC Elementary Student Science Project Consulting (2016)
SCW: Space Cryogenics Workshop (every 2 years)
CEC: Cryogenics Engineering Conference (every 2 years)
AIAA Aerospace Sciences Meeting (annually)
AIAA Summer Thermophysics Conference (annually)
Tour of Cryogenics and Thermal laboratory facilities to ASME
HTFEICNMM conference (2016)
 CEC Organizing Committee (Dr. Michael J. Dipirro)
 American Editor for Elsevier’s Journal of Cryogenics (Dr. Peter
Shirron).
 AIAA Thermophysics Technical Committee Past Chair (Dr. Eric A. Silk)
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Outreach Activity Photos
2014 USA Science &
Engineering Festival
Goddard Science
Jamboree
LN2 Ice Cream:
Before
40
LN2 Ice Cream:
After
NASA Goddard Contractors Association
September 8, 2016 Greenbelt, MD., 20771, USA
Conclusions
 Code 552 provides world class expertise in the design and
development of low temperature cooling systems for
spaceflight applications.
 We welcome partnerships across NASA, the government, the
education community and private industry.
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Thank You
Branch Head: Eric A. Silk
6-8205
[email protected]
Assoc. Branch Head: Hudson Delee
6-9091
[email protected]
Branch Secretary: Saiqa Huda
6-5405
[email protected]
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Questions
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Extras
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Titanium Shell Body Heat Switch
Larger body allows larger surface area
for higher on-conductance
Shell body Ti 15-3-3-3; ~0.127 mm
(0.005 inch) thick
NASA Goddard Contractors Association
September 8, 2016 Greenbelt, MD., 20771, USA