incubator designs for space flight application ... incubator designs for space flight application...
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Incubator Designs for Space Flight ApplicationOptimization and Automation
A. Hoehn, J. B.Freeman, M.Jacobson, L.S.StodieckBioServe Space Technologies, University of Colorado
SAE paper 1999-01-217729th International Conference on Environmental Systems
July 11-15, 1999, Denver, CO
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Space Shuttle Experiment Accommodation
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Experiment Accommodationenvironmental control / experiment execution
BPCS
Auto-GAP ICV
GEFA
GBA_ICM
M-FPA
GE-FPA
FPA
Isolate Gravity as sole independent variable:uniform ground vs.. flight environment / centrifuge ?temperature most influential, but: launch / landing, moisture, atmosphere
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Typical Thermoelectric Heat Pump Assembly
Temperature-Controlled Device•water-, air-heat exchanger, device
Thermoelectric Heat Pump
Air Heat Exchanger
Forced Convection Cooling
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Required Heat Pump Capacity
Required Heat Pump CapacityFor 4 Different Ambient Temperature Levels
-20
-10
0
10
20
30
40
50
0 5 10 15 20 25 30 35 40
Incubator Temperature [°C]
Hea
t Pum
p C
apac
ity [W
]
20°C T amb25°C T amb
30°C T amb
35°C T amb
12 mm foam insulation
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Heat Pump Optimization
TEC Electric Configuration Effectsfor 5 different TEC Modules
0.00
20.00
40.00
60.00
80.00
100.00
2S 3S 4S2S
x2P 5S 6S
4Sx2
P
Configuration (serial, parallel)
Elec
tric
Pow
er [W
] per
40
Wat
t Hea
t Pum
p C
apac
ity
Type A
Type B
Type C
Type D
Type Ec
TECTECTECTEC
TECTECTEC TEC
V+
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Forced Convective Cooling ?
•Densely packed•Larger temperature gradientsdue to heat transport
Option:•Water-cooled walls•External Insulation•High thermal Conductivity
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PGBA Thermal Management Subsystem
Solid state Peltier devices used to “pump” heat from liquid loops to air heat exchanger
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Temperature Gradients - Heat Transport
Heat Transport in Water
0
1
2
3
4
5
6
0 10 20 30 40Incubator Temperature [°C]
Del
ta T
empe
ratu
re (E
ntra
nce
- Exit
) [°
C]
100 ml/min
200 ml/min
300 ml/min
400 ml/min
Difference between entrance and exit coolant temperature
30°C ambient temperature12 mm foam insulation
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Temperature Transients
•Loading•Power Loss•Transport•New Setpoint
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Internal Heat Sources - Gradients
STS-93 STARS Payload:(Space Technology and Research Students)
Middle and High Schools across US and Chile participate.STARS-1 based on experiment proposed by students in ChileSPACEHAB Inc., a number of schools and other organizations participatingHardware Highlights:
» 5 habitat for plants, aphids, ladybugs, butterflies
» 10 high resolution color cameras / frame grabber
» active temperature control» passive humidity and gas control
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Light as heat source
Radiant heat transfer:» 1-3degC temperature increase» provide conductive pathways» water-cool directly
Illuminated Cultures:
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Individually Controlled Experiment Accommodationtemperature profiles for automated experiment activation and termination
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Liquid Coolant Loop9 individual PID controllers under power limit (130 Watt)
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Individual Temperature Profile Controllag due to thermal mass
0
5
10
15
20
25
30
35
40
-180 0 180 360 540 720 900 1080
MET (min)
Tem
p (°
C)
AavgBavgCavgDavgEavgFavgGavgHavgAhoboBhoboChoboDhoboEhoboFhoboGhoboHhobo
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Incubator Future
Better insulation: vacuum panels, aerogels» power reduction» longer unpowered times (ISS: 2 hrs.)
Unpowered temperature control:» phase change materials» vacuum insulation
Transport to / from ISS:» longer temperature stability, even unpowered
STS-93 7/20/99
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AcknowledgementsIncubator Designs for Space Flight Application
Optimization and Automation
Brian Biesterfeld, Jim Clawson, Jake B.Freeman, Jon Genova, Don Geering, Kevin Gifford, Mindy
Jacobson, Brett Landin, Diane Naylor, Mark Rupert, Steve Schneider, Dave Simmons, Louis S.Stodieck
BioServe Space Technologies, University of Colorado
NASA grants: NASA-MAR: NCC8-131 (NASA MSFC cooperative agreement) and NASA-NCC2-5290 (NASA Ames cooperative agreement).
Debra Reiss-Bubenheim, Rudi Aquilina, Shawn Bengston, Steve Patterson, NASA Ames Research Center
SAE paper 1999-01-2177