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Thermal Analysis of Passive Radiator for Inter-Planetary Space Applications
Presented By
Shailesh Kumar Singh Rajput
Abhishek DorikYash Dave
Bijank ModiDipak Patel
Guided ByProf. Harshal Shukla
OverviewLiterature SurveyPaper PresentedObjectiveIntroductionATCS & PTCSEnvironmental LoadsGoverning Equations Modeling, Simulation and Boundary ConditionsResultsConclusionsAnnexure
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Sr. Paper / Book Author / Editor Conclusions
1Spacecraft Thermal Control HandbookVol. 1: Fundamental Technologies.
David G. Gilmore
Basics of Thermal control systems, Space Radiators and Environmental Loads and Operating conditions of the Satellite.
2Design of Geosynchronous Spacecraft
Brij N. Agrawal
Thermal control of Spacecraft, Heat Transfer governing laws and different types of Thermal Control Strategies.
3Thermal Control System of the Moon Mineralogy Mapper Instrument
Jose I. Rodriguez(JPL)
Passive Thermal Cooling Systems, Coatings, MLI
4The Moon Mineralogy Mapper (M3) on Chandrayaan-1
Alok Chatterjee (JPL)
Multi Layer Insulation (MLI)
Literature survey
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Paper PresentedPresented Paper Titled:
“Thermal Analysis of Passive Radiators for Inter-Planetary Space Applications”
In the International Conference:“Engineering: Issues, Opportunities and
Challenges for Development”On: Saturday, 9th April, 2016
ISBN: 978-81-929339-3-1
objective
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Conduct Parametric analysis to understand the effects of change in the values of parameters like Radiator Area and Thickness over the heat transfer rate from a Satellite.
We aim at providing suitable design guidelines for maximizing the dissipation of heat generated inside the satellite to space by using passive radiators.
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Introduction
Thermal Control SystemActive Thermal Control System
Passive Thermal Control System
Allowable Temperature LimitsHeat Produced by Electronic Systems
Heat MUST be dissipated to spaceHOW??
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Active THERMAL CONTROL SYSTEM(ATCS)
Used where Narrow Temperature range are to be maintained
Uses electric power input
Heaters, coolers, coolant storage system used
Moving Parts and fluids involved
Heavy and costly cooling system
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PASSIVE THERMAL CONTROL SYSTEM(PTCS)
NO Moving Parts
NO Moving Fluids
NO Electric Power Input
Geometrical Configurations
Thermo-Optical Properties of Surface
Thermal Insulations
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Environmental LoadsSolar Flux
Direct sunlight is the dominating source of heating on the satellite surface.
AlbedoIt is the sunlight reflected off a planet’s surface.
Planet ShineInfrared energy emitted by a planet by the virtue of its own temperature.
SOLAR FLUX
PLANET SHINE
ALBEDO
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Governing EquationsSteady - stateHeat Balance Equation:
[Heat Radiated] = [Heat Absorbed]+[Instrumental Heat Dissipation]
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Governing EquationsTransient state
Based on Lumped Parameter Analytical Method, Heat Balance equation for each node:
Neglecting Albedo and Earth Radiation
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Case Study: Flat Plate Radiator Modeling of Radiator
DissipatorFlat Plate Radiator
Thermal StrapPackage bodyWith MLI
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Device Material Dimensions (mm)
Thermo-optical Properties
IR Solar
Package Aluminium 6061
300×150×300 - -
Dissipator Stainless Steel 30×40×50 - -Thermal
Strap Copper - - -
Radiator Aluminium 6061 (Variable) ε =
0.85 α = 0.4
MLI - - ε = 0.7 α = 0.45
model specifications
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Meshing and simulation
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Bottom face of Package = 20o CThermal Coupling between Dissipator and base
of package: R= 60 C/WThermal Coupling between Dissipator and
Thermal Strap: h= 300 W/m2 CThermal Coupling between Thermal Strap and
Radiator: h= 300 W/m2 CCoupling between MLI and Package: h=0.03
W/m2 C
Boundary conditions applied
300×150×2; Q=3.75 WSr. No. Part Min. Temp Max. Temp
1 Radiator 596.70 602.432 Dissipator 514.15 544.053 Thermal Strap 547.22 581.224 Package 20.00 59.00
results
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resultsSr. Dimension Part
Steady State Condition Transient ConditionsDissipation
Min. Temp Max. Temp Min. Temp Max. Temp
1 300*150*2
Radiator 596.70 602.43 20.00 208.02
3.75Dissipator 514.15 544.05 20.00 189.18
Thermal Strap 547.22 581.22 20.00 197.53
Package 20.00 59.00 20.00 72.17
2 300*150*2
Radiator 1299.19 1304.88 20.00 412.61
15Dissipator 1182.87 1254.07 20.00 442.06
Thermal Strap 1255.83 1283.72 20.00 420.57
Package 21.52 59.00 20.00 72.17
3 300*150*3
Radiator 596.85 600.64 20.00 218.95
3.75Dissipator 514.15 544.05 20.00 204.79
Thermal Strap 547.22 581.22 20.00 213.78
Package 20.00 59.00 20.00 72.17
4 300*150*3
Radiator 1299.33 1303.12 20.00 401.73
15Dissipator 1182.86 1254.06 20.00 441.77
Thermal Strap 1248.06 1283.70 20.00 419.45
Package 20.00 59.00 20.00 72.17
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resultsSr. Dimension Part
Steady State Condition Transient ConditionsDissipation
Min. Temp Max. Temp Min. Temp Max. Temp
5 350*200*2
Radiator 725.24 733.14 20.00 240.82
3.75Dissipator 612.27 653.20 20.00 221.75
Package 20.00 58.30 20.00 71.60
Thermal Strap 667.76 704.12 20.00 233.65
6 350*200*3
Radiator 725.44 730.664 20.00 229.62
3.75Dissipator 612.26 653.19 20.00 215.28
Package 20.00 58.30 20.00 71.60
Thermal Strap 657.76 704.11 20.00 224.12
7 350*200*3
Radiator 1426.30 1431.52 20.00 403.00
15Dissipator 1281.50 1360.46 20.00 448.73
Package 20.00 58.30 20.00 71.60
Thermal Strap 1357.05 1404.97 20.00 426.49
8 500*300*2
Radiator 1394.21 1420.11 20.00 417.74
3.75Dissipator 1192.14 1295.43 20.00 372.99
Package 20.00 57.46 20.00 70.85
Thermal Strap 1306.80 1339.83 20.00 389.14
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resultsSr. Dimension Part
Steady State Condition Transient ConditionsDissipation
Min. Temp Max. Temp Min. Temp Max. Temp
9 500*300*2
Radiator 2092.17 2109.45 20.00 515.14
15Dissipator 1861.90 1988.10 20.00 520.01
Package 20 57.46 20.00 70.85
Thermal Strap 2003.82 2037.24 20.00 505.82
10 500*300*3
Radiator 1394.75 1412.03 20.00 374.09
3.75Dissipator 1192.14 1285.43 20.00 339.37
Package 20.00 57.46 20.00 70.85
Thermal Strap 1306.80 1339.82 20.00 353.07
11 500*300*3
Radiator 2092.17 2109.45 20.00 515.14
15Dissipator 1861.90 1988.10 20.00 520.01
Package 20 57.46 20.00 70.85
Thermal Strap 2003.82 2037.24 20.00 505.82
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Conclusions1. For small Heat Dissipation from Instruments, Passive
Radiator cooling can be very effective and economical.
2. Increasing the surface area of the radiator does not increase the heat transfer from the satellite.
3. Increased Surface Area Increased Incident Load Reduced Heat Transfer.
4. Increasing the thickness of the radiator does not increase the heat transfer from the satellite.
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Validation of Results and Conclusions
Spacecraft Thermal Vacuum Test
Infrared Simulation
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references1. Spacecraft Thermal Control Handbook, Vol.1; Fundamental Technologies,
Chapter 1-6, David G. Gilmore, Pages 1-222.2. Thermal Control System of the Moon Mineralogy Mapper Instrument, Josh I
Rodriguez, Jet Propulsion Laboratory, California Institute of Technology.3. “The Moon Mineralogy Mapper (M3) on Chandrayaan-1” by Alok Chatterjee,
Padma Varanasi.4. “The Moon Mineralogy Mapper (M3) for lunar science” by A. Chatterjee,
Padma Varanasi, A.S.K Kumar.5. “Thermal Control System of the Moon Mineralogy Mapper Instrument” by
Jose I. Rodriguez, Jet Propulsion Laboratory, California Institute of Technology.
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Radiator size calculator (Java netbeans 8.0.1)
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Code for radiator
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Thank You.