tfaws active thermal paper session · 2019. 5. 20. · thermal control system (eatcs) radiator #3...
TRANSCRIPT
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Ammonia Vent of the External Active
Thermal Control System (EATCS)
Radiator #3 Flow Path #2 on the
International Space Station (ISS)
Darnell Cowan
NASA JSC ATCS
Presented By
Darnell Cowan
Thermal & Fluids Analysis Workshop
TFAWS 2018
August 20-24, 2018
NASA Johnson Space Center
Houston, TX
TFAWS Active Thermal Paper Session
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Overview
• Background
• EATCS Overview
• International Space Station
• Venting Analysis Problem Definition
• Modeling
• Assumptions
• Analysis Results
• On-Orbit Operations Recommendations
• Comparison to On-Orbit Operations
• Vent Video
• Summary
• Backup– Acknowledgments
TFAWS 2018 – August 20-24, 2018 2
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Background
• Robotic External Leak Locator
(RELL) scans found higher
concentrations of vaporous
ammonia near the EATCS Loop
B Radiator #3 Flow Path #2
• On May 3, 2017, the EATCS
Loop B Radiator #3 Flow Path
#2 was isolated and vented
• As of the data to date, the
ammonia leak has ceased
• The purpose of this presentation
is to discuss the analysis for
venting the EATCS Loop B
Radiator #3 Flow Path #2
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• The External Active Thermal Control System (EATCS) provides active cooling for all pressurized
modules and the main Power Distribution Electronics (PDE) on the International Space Station
(ISS) – 2 EATCS loops (Loop A and Loop B) each of which includes 3 deployable radiators
– Each deployable radiator contains 2 flow paths to provide heat rejection
• Telemetry monitoring identified a coolant (liquid ammonia) leak in EATCS Loop B
EA
TC
S L
oop B
Am
monia
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Nitrogen
Tank
EATCS Overview
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EATCS Loop B Simplified Schematic
FCV
S0-
RAD
DeployedP1-3
Heaters
PDE 1
JEM
MT HX
PDE 3 PDE 4
PDE 2
Node 2
LT HX
Node 3
LT HX
USL
MT HX
Ammonia Tank
Pump
GN2NH3
Key:
LT=Low Temperature
MT=Moderate Temperature
PDE=Power Distribution Electronics
FCV=Flow Control Valve
COL=Columbus Module
JEM=Japanese Experiment Module
USL= US Laboratory
HX= Heat Exchanger
COL
LT HX
PDE 5
Radiator #1
RAD
DeployedP1-3Radiator #2
RAD
DeployedP1-3Radiator #3
GN2NH3
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International Space Station (ISS)
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International Space Station
http://zombie.wikia.com/wiki/The_International_Space_Station_(ISS)
EATCS Loop B
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Venting Analysis Problem Definition
• Ammonia venting analysis is performed to determine:
– Time to empty the flow path– Thrust imposed on the ISS
• The plan was to isolate the ammonia from the EATCS Loop B Radiator #3 Flow Path #2 from the rest of the EATCS, then vent the isolated volume to space
• Any residual ammonia left in the radiator could cause hydrostatic lockup (no compliance) resulting in potential hardware damage
• Furthermore, excessive thrust could cause the ISS to lose attitude control
• Flight controllers and engineers in the Mission Control Center (MCC) used this data to develop operational procedures and safety measures to perform the vent
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Radiator Beam Valve Module
http://spaceflight101.com/iss/iss-us-eva-49-preview/
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Modeling
• Mathematical model in Excel
• Radiator flow path was modeled as a
lumped reservoir – Used the worst case temperatures to represent
the entire Radiator Flow Path (~ 1 ft3)
• Ammonia vents through a small pipe
without friction directly to space and
choked at the exit – Radiator Flow Path is vented through a Tee
• Reservoir is initially a liquid
• The vent begins as a isothermal process
until the system reaches saturation (2-
phase)
• Once the reservoir reaches saturation, the
vent continues via isentropic expansion– No heat transfer
– Pressure decreases the temperature
decreases to maintain constant entropy
• Thrust and time to vent can be calculatedTFAWS 2018 – August 20-24, 2018 7
Vent Valve
Vent Model
Liquid Vapor
Vent Tee
Reservoir
F=Thrust
t=time
F,t
F,t
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Additional Calculation for Thrust
• Liquid vents begin at a quality of 0 and throughout the vent the
void fraction increases until it eventually reaches a quality of 1,
this produces two independent venting regimes.
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• Void Fractions < 0.5– Liquid vent is driven by
mechanical energy (pressure)
• Void Fractions > 0.5– Liquid vent is driven by
both mechanical energy (pressure) and thermal (temperature) energy
• liquid vent reaches the “dispersed flow” two phase regime and the liquid slugs are accelerated by the compressible gas bubbles
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Assumptions
• Initial EATCS Loop B Radiator #3 Flow Path #2 pressure was
based on the maximum operating pressure requirement of
390 psia (2689 kPa)
• Initial EATCS Loop B Radiator #3 Flow Path #2 temperatures
for time to vent and thrust were based on the worst case
coldest and hottest operational temperatures observed on-
orbit over the past 2 years
– Coldest temperature ~ -40 Deg F (-40 Deg C) drives maximum vent
duration
– Hottest temperature ~ 55 Deg F (13 Deg C) drives maximum thrust
• Telemetry sensor error and temperature and pressure swings
due to orbital environmental changes are neglected
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Analysis Results
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EATCS Loop B Radiator #3 Flow Path #2 Pressure vs Time Plot
Based on initial Pressure and Temperature of 390
psia (2689 kPa) and -40 Deg F (-40 Deg C)
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Analysis Results
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EATCS Loop B Radiator #3 Flow Path #2 Thrust vs Time Plot
Based on initial Pressure and Temperature of
390 psia (2689 kPa) and 55 Deg F (13 Deg C)
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On-Orbit Operation Recommendations
• Summary– Worst case time to empty the EATCS Loop B Radiator #3 Flow
Path #2 was ~ 60 minutes
– The predicted maximum thrusts were ~ 11 lbf (49 N) at the start
of the vent and ~10 lbf (45 N) after the system reaches
saturation
• Recommendation– For vent times,
• ATCS recommended leaving the EATCS Loop B Radiator #3 Flow
Path #2 in the vent position for no less than 24 hours to ensure all
the ammonia is evacuated
– For thrust,
• Recommend using Russian Thrusters to maintain ISS Attitude
Control
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Comparison to On-Orbit Operations
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Figure 9: Predicted vs Actual EATCS Loop B Radiator #3 Flow Path #2 Pressures
Predicted results bounded the actual
results
Predicted using data at the time of the vent
Initial Pressure = 316 psia (2179 kPa)
Initial Temperature= 48 Deg F (9 Deg C)
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Vent Video
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• EATCS Loop B Radiator #3 Flow Path # 2 Vent Video
available via YouTube
– https://youtu.be/PJzjs4EI22k?list=PL4Bmr2TXQTcQnxXpZ7BkG
k_t0IhTByrDy
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Summary
• Predictive analysis determined the worst case time to empty the EATCS Loop B
Radiator #3 Flow Path #2 was ~ 60 minutes
• Telemetry indicated that the system reached saturation almost instantaneously
and took ~ 20 minutes to empty the EATCS Loop B Radiator #3 Flow Path #2
• Using telemetry from the day of the vent, analysis determined the time to empty
the EATCS Loop B Radiator #3 Flow Path #2 would be ~13 minutes
• The original predictive analysis used worst case inputs and assumptions which
bounded the actual results
• The maximum thrust initial time of the vent and during 2-phase were ~ 11 lbf (49
N) and ~10 lbf (45 N)
• Telemetry is not available to correlate actual thrust with the predicted maximum
thrusts
• However, by using Russian Thrusters for ISS attitude control, attitude control
telemetry indicated the flight attitude was maintained
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Backup
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Acknowledgments
• Would like to acknowledge the outstanding work of the
Flight Operations Directorate (FOD) and Mission
Evaluation Room (MER) engineering teams
– Particularly the following:
• The Boeing Company - Houston Active Thermal Control (ATCS)
and Passive Thermal Control Systems (PTCS) team
• FOD - Station Power, Articulation, Thermal, and Analysis
(SPARTAN) group
• NASA – Johnson Space Center (JSC) Active Thermal Control
System (ATCS) team
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