An advanced weapon and space systems company 1 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21 st Annual AIAA/USU Conf. on Small Satellites Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites David Bugby ATK Space Beltsville, MD 21 st Annual AIAA/USU Conference on Small Satellites
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An advanced weapon and space systems company
1 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites
David Bugby
ATK SpaceBeltsville, MD
21st Annual AIAA/USU Conference on Small Satellites
An advanced weapon and space systems company
2 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
PREVIEW QUESTIONS
Ground Testing of ME-HLHPBased Cooling Systems for ...
- Smallsats (NASA ST-8)- Five Additional Applications
> Laser Diode/Crystal> Compact Laser> Large Spacecraft> Electronics > Instruments
5 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
• OBJECTIVE: Develop two-phase loop thermal management system (TMS) toreplace the traditional "cold-biasing plus heater power" approach, to enable ...
- Flexibility in component placement- Reduced mass / heater power / volume- Improved power resource efficiency- Scalability from 150 kg, 200 W nominal size
• PAPER / BRIEFING: Describes a two-phase loop based cooling system for smallsats developed during a 6-month ST-8 study and 5 subsequent ground tested cooling systems for lasers, spacecraft, electronics, and instruments.
INTRODUCTION
MLI Covers Non-Radiator Surfaces
High Power ComponentsMounted On/Near Exterior
(may need heater power when OFF)
Earth-Viewing ComponentsNeed Heater Power When OFF
Internal Components Coupled Conductivelyand/or Radiatively to the Walls
Radiator 2Sized/Coatedfor Hot Case
IncludingHot Radiator 1
Space-Viewing ComponentsNeed Heater Power When OFF
Radiator 1Sized/Coatedfor Hot Case
IncludingHot Radiator 2
CBHX
All Components Except External Viewing OnesCentrally Located Coupled to ME-HLHP Thermal Bus
Total MLI Coverage Except ProtrudingComponents, Lines, Standoffs
Radiator 1Sized/Coated forHot Case ... CanIgnore Impact ofHot Radiator 2
Subcooler 2
Radiator 2Sized/Coated forHot Case ... CanIgnore Impact ofHot Radiator 1
DHPto CBHX
Earth-Viewing ComponentsKept Warm When OFF by HLS
Space-Viewing ComponentsKept Warm When OFF by HLS
Subcooler 1 DHPto CBHX
Two-Phase Loop TMSCold-Biasing Plus Heater Power TMS
... NASA ST-8 requirements(for future missions especially those with
extended eclipses and limited power)
An advanced weapon and space systems company
6 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
BACKGROUND
• Requirements (ST-8)enable component placement flexibilityminimize power/mass/volumeimprove power resource efficiencyscalable from 150 kg, 200 W nominal size
7 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
RATIONALE
FEATURE WHAT IT DOES WHY IT'S GOOD
Multi-Evaporator BusDecouples structure and thermal
design process so component placement is more flexible
Simplifies Design,Reduces Mass
Heat Load Sharing Keeps environmentally exposed instruments warm when not "ON"
Reduces Heater Power,Improves Efficiency
Miniaturized Components
Reduces weight ExpandsPackaging Options
Thermal Diode Action Isolates payload/components from extreme environments
ExpandsMission Options
Multiple Condensers Reduces need to adjustattitude for thermal control
Increased TimeAvailable for Science
Set-Point Controllability
Reduces payload/componenttemperature fluctuations
Minimizes Temperature Cycling, Lengthens Life
High Conductance Enables centralized component mounting configurations
Shorter Electrical Harnessing, Simpler
Structure, Reduced Mass
An advanced weapon and space systems company
8 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
CONCEPT
An advanced weapon and space systems company
9 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
DESIGN
Counter-FlowCondenser 2
SweepageSight Glasses
Liquid
Counter-FlowCondenser 1
EVAP 3(Heat Load Sharing)
Single-PhaseSweepage Vapor
EVAP 1
Cold-BiasedHeat Exchanger(CBHX)
EVAP 2EVAP 4
SecondaryEvaporator
Chiller Lines
Reservoir Shunt
BPR
Subcooler
Subcooler
Reservoir
Two-PhaseSweepage
Counter-FlowCondenser 2
SweepageSight Glasses
Liquid
Counter-FlowCondenser 1
EVAP 3(Heat Load Sharing)
Single-PhaseSweepage Vapor
EVAP 1
Cold-BiasedHeat Exchanger(CBHX)
EVAP 2EVAP 4
SecondaryEvaporator
Chiller Lines
Reservoir Shunt
BPR
Subcooler
Subcooler
Reservoir
Two-PhaseSweepage
An advanced weapon and space systems company
10 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
TESTING
• RESULTS: With ammonia as the working fluid, 21 tests were carried out with the ST-8 ME-HLHP test loop resulting in:
quad-evaporator transport of 8-280 Wsingle-evaporator transport of 2-100 Wpower cycling from 50-200 Wmaximum heat flux of 30 W/cm2
conductance of 5-8 W/K per evaporatorheat load sharing greater than 95%condenser switchingfreeze-tolerant condenserset-point control to +/- 0.25 Krapid start-upsweepage evaporator power of 4Wdiode action/loop isolationTeflon evaporator 233-353 K cycling
• STATUS: All 21 tests successful ... key accomplishment was the development of a 5 μm miniaturized Teflon wick evaporator. Despite success, dual-evaporator LHP with TEC reservoir cold-biasing selected for flight experiment. Concerns ...
the risk of expanding beyond two evaporatorsthe impact of TEC failure on loop temperature controllability
Miniaturized Al BodyTeflon Wick Evaporator
5 cm
Wick 0.63 cm OD5 micron pore size
10
15
20
25
30
35
40
18:30 19:00 19:30 20:00 20:30 21:00 21:30 22:00
Time [hh:mm]
Tem
pera
ture
[C]
0
50
100
150
200
250
300
Hea
t Loa
d [W
]
Reservoir inlet (1) Reservoir (4) 2nd pump (6) BPR outlet (14)FR outlet (43) Liquid line (45) E2 body (52) E3 body (57)liquid sweepage line (68) vapor sweepage line (73) ambient (80) 2nd pump [W]E2 Power [W] E3 power [W] Total Evap Power [W]
Reservoir inlet (1) Reservoir (4) 2nd pump (6) BPR outlet (14)FR outlet (43) Liquid line (45) E1 body (48) E2 body (53)E3 body (57) E4 body (62) liquid sweepage line (68) vapor sweepage line (73)ambient (80) Q-meter (82) Q-meter (83) 2nd pump [W]E1 Power [W] E2 Power [W] E3 power [W] Total Evap Power [W]
DIODE ACTION
POWER CYCLING
10
15
20
25
30
35
40
45
6:00 6:30 7:00 7:30 8:00 8:30
Time [hh:mm]
Tem
pera
ture
[C]
0
50
100
150
200
250
300
350
Hea
t Loa
d [W
]
Reservoir inlet (1) Reservoir (4) 2nd pump (6) BPR outlet (14)FR outlet (43) Liquid line (45) E2 body (52) E3 body (57)liquid sweepage line (68) vapor sweepage line (73) ambient (80) 2nd pump [W]E2 Power [W] E3 power [W] Total Evap Power [W]
Reservoir inlet (1) Reservoir (4) 2nd pump (6) BPR outlet (14)Liquid line (45) E1 body (47) E2 body (52) E3 body (58)E4 body (62) ambient (80) Cond #2 (25) Total Evap Power [W]
SET-POINT CONTROL
An advanced weapon and space systems company
11 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
APPLICATIONS
Four Parallel Condenser Lines
Flow Regulator (4)
Liquid Header
Condenser Vapor Header
Back Pressure Regulator (BPR) Secondary Evaporator
13 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
APPLICATIONSINTERMITTENT-POWER INSTRUMENT COOLING
Dual-Cascaded Loop, 0-400 W 4-Evap. Instrument Side ME-HLHP, 100 W Avg. 1-Evap./2-Condenser Radiator Side HLHP
Instrument-Side Valves to Enable 3 vs. 4 Port ME-HLHPSweepage Plumbing and Enhanced Reservoir Transient Operation(5X Regular Valves, 2X Check Valves [CV], Test Only)
4. TEC Reservoir Cold-Biasing5. Parallel or Series Plumbing
An advanced weapon and space systems company
14 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
APPLICATIONS
SUMMARY OF ME-HLHP GROUND TESTING
5
Diode
2
1a 1b 2 3a 3b 4 5a 5b
5002000
Compact
An advanced weapon and space systems company
15 Multi-Evaporator Hybrid Two-Phase Loop Cooling System for Small Satellites 21st Annual AIAA/USUConf. on Small Satellites
CONCLUSION
OVERALL: This briefing has described the development and testing of a multi-evaporator two-phase loop based cooling system for small satellite thermal control.
TECHNOLOGY BASIS: Multi-evaporator hybrid loop heat pipe (ME-HLHP), a two-phase loop cooling system with CPL and LHP underpinnings, but with key advantages over each.
PRIMARY APPLICATION: Cooling system designed/built/ground-tested as part of the NASA ST-8 Phase A study from Jan-Jun 2004. At that time, it was the first-ever ground test of a miniaturized ME-HLHP cooling system.
ADDITIONAL APPLICATIONS: The design and successful ground testing of five subsequent ME-HLHP based cooling systems -- in the areas of laser, spacecraft, electronics, and instrument cooling -- were also described.
FLIGHT EXPERIMENT: The ME-HLHP architecture has clearly been proven through extensive ground testing for a variety of applications ... to fully validate it for future smallsat missions, an ME-HLHP flight experiment is needed !
NOTE: Paper Was Originally a Backup for Session X, so its file name on the Proceedings CD is SSC07-X-11.pdf