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TANK PRESSURE CONTROL EXPERIMENT (TPCE)
Flight Experiments Technical Interchange Meeting October 6.1
Mike Bentz Boeing Defense & Space Group
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TANK PRESSURE CONTROL
EXPERIMENT OVERVIEW ~
• Tank Pressure Control Experiment (TPCE) is a small self-contained STS payload
• Objective is to test jet mixer for cryogenic fluid pressure control ..
• Flown on STS-43 in August 1991
• Demonstrated reliable pressure control with low-energy mixer
• Reflight scheduled for late October on STS-52
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TANK PRESSURE
CONTROl. EXPERIMENT PROJECT ORGANIZATION
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• Sponsored by In-Space Technology Experiments Program (In-STEP)
• Managed by NASA Lewis Research Center
• Design, fabrication, flight data analysis by Boeing Defense & Space Group
• STS integration managed by NASA Goddard Space Flight Center
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TANI( PRESSURE CONTROL '
EXPERIMBN PROJECT PHILOSOPHY /
• Quick-response, relatively low-cost experiment
• GAS carrier chosen for ease of integration, manifesting
• Class D Modified approach used for hardware development
- minimum cost
- commercial-grade components
- reduced product assurance requirements (except safety)
- extra system-level testing to assure of flight readiness
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TANK PRESSURE co o
ENT RISK MANAGEMENT APPROACH /
• Designed with redundancy where most beneficial -. • Designed for minimal requirements on Orbiter and crew
• Based designs and components, where possible, on those used on prior payloads
• Tested prototype in low-g on Lewis Learjet Microgravity Test Facility
• Performed five complete Mission Simulation tests prior to delivery
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TANK PRESSURE CONTRa
EXPERIMENT PROBLEM AND OBJECTIVES /
Problem:
Storage of cryogens for long durations in low-g requires efficient and reliable control of tank pressure.
Active jet mixing is leading candidate for pressure control but energy addition results in boiloff penalty. Low-energy mixing requires in-space test.
Objectives:
• Detennine jet mixing effectiveness in realistic low-g environment as measured by ability of jet to: • penetrate vapor bubbles and reach all tank regions • reduce pressure in minimum time / minimum energy • eauilibrate fluid temperatures
• Provide data for development of analytical models
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TANK PRESSURE CONTROL
EXPERIMENT APPROACH
• Refrigerant 113 simulates cryogens '.
• 0.5 cu-ft tank filled to 83% level
• Pressure raised by heating, then reduced by mixing
• 38 test runs to detennine effect of flow rate, acceleration environment, heater location
• Packaged as an autonomous STS payload using GAS carrier
TANK PRESSURE CONTR EXPERIMENT PAYLOAD CONCEPT
BOEING--------------------------------------------------------------Com
Composlt. structur.
Pr.ssur. transducer
Pressure switch
CUlaway View
Batteries (48)
N'ote: For clarity .. soma components aro not shown In their truo orlontallon:)
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. TANK PRESSURE CONTROL
. ~T~ MI~~ION PLAN EXPERIMENT _ • _ •••• __
EJOSNG
• Secondary payload using Get-Away Special carrier
• Payload size: <200 Ibm, 5.0 cu-ft
• Tank major axis aligned with Orbiter
X-axis, mixer nozzle at aft end
• OMS burns will settle liquid at mixer end
• Tail-first Orbiter orientation during first
sleeping period (8 hours)
• Payload activation by baroswitch during launch
• Test duration: approximately 27 hours
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rANK PRESSURE CON
SUMMARY OF DATA· VIDEO
• Effects of acceleration environment
• Heating (pressure rise) phase
• Self-mixing behavior
• Mixing flow patterns
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CONTRa EXPERIMEN
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rANI( PRESSURE CONTROl.
EXPERIMEN RESULTS AND CONCLUSIONS ~
• All objectives met or exceeded, no failures
• Data support thesis that low-energy jet is efficient pressure control device • I
- Moderate velocities cause comDlete circulation, rapid pressure drop
- Low velocities also cause reliable pressure drop with -80% less energy added
- Identified ranges of dimensionless jet momentum to be avoided
- Generated large amount of digital and video data to support model development
• Identified potentially significant pressure rise phenomena requiring further stud
• Payoff: - Cryogen pressure control shown to be manageable problem
- Boiloff mass due to mixing can be reduced to insignificant level
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