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HokieSat Thermal System
Michael BelcherThermal Lead
December 11, 2002
Introduction
• Thermal modeling
• Software
• Calculations
• Results from analysis
• Conclusions
• Future plans
Heat Transfer Fundamentals
• Convection• Q = hconvectionA(T)
• Conduction• Q = G(T)
• Radiation• Q = A (T2
4-T14)
• Heat transfer in space occurs through conduction and radiation only
Thermal Model
• Predicts temperatures of spacecraft components
• Identifies problem areas
• Useful in analyzing existing design
• Usually software based• TSS, SINDA, TRAYSIS, SSPTA, I-DEAS
SSPTA
• Simplified Space Payload Thermal Analyzer
• Evaluation/ Educational Software from Swales Aerospace
• Consists of several smaller programs, which calculate view factors, radiation couplings, absorbed heat loads
• Used in conjunction with SINDA
SINDA
• Systems Integrated Numerical Differential Analyzer
• Freeware
• Calculates temperatures based on a network of thermal nodes
• Solves network using finite difference method
SSPTA Models
SSPTA Models
SSPTA Models
Radiation Surface Properties
Irridite Aluminum 0.01 0.11
300 Series Stainless Steel 0.47 0.14
Delrin AF 0.96 0.87
GaInP2/GaAs/Ge (Solar Cells) 0.92 0.85
Ultem 2300 (PPTs) 0.3 0.3
Conduction Couplings
• Calculated in Excel
• Q = G(T)
• G = hA
• Value of h dependant upon:• Interface type• Conduction coefficient
Conduction Couplings
h (W/m2°C)
Interface type Low High
Bolted 300 1000
Pressure contact 15 30
Thermal interface filler 10,000 15,000
Thermal Models
• Created separately for independent verification and ease of use
• Stand-alone models• Battery box• CEE• External
• Integrated model• Internal, external, battery box, CEE
Hot and Cold Case Parameters
Hot Cold
Peak powerrequirements
Average powerrequirements
Maximum orbitalincident fluxes
Minimum orbitalincident fluxes
Model Results: CEE
• Preliminary results showed need for a thermal filler around bolted interfaces
Component
Min Ave Max Cold Hot
Boards 35.2 38.3 46.6 -40 80
Cells 30.0 30.0 30.2 -40 80
Predicted Temps (°C) Operational Limits
Overall Model: Cold Case
Component
Min Ave Max Cold Hot
Batteries 43.2 43.8 44.6 5 20
Boards 20.6 24.0 32.0 -40 80
PPU 11.8 19.1 24.7 -55 125
PPT Capacitors -28.1 -13.1 6.6 N/A 125
Thrusters -26.8 -10.7 10.4 -40 100
Predicted Temps (°C) Operational Limits
Overall Model: Cold Case
Component
Min Ave Max Cold Hot
Cameras -25.2 3.3 53.7 -20 60
Rate gyros 10.3 11.4 12.6 -40 80
Magnetometer -8.7 20.0 51.2 -40 85
D/L transmitter 16.4 36.3 61.9 -20 70
U/L receiver 6.4 33.3 52.2 -20 70
Predicted Temps (°C) Operational Limits
Overall Model: Cold Case
Component
Min Ave Max Cold Hot
GPS filter -8.3 3.8 20.7 0 50
GPS isolator -18.1 -16.2 -14.3 0 50
GPS NCLT 21.4 21.6 21.8 0 50
GPS preamp -7.9 4.0 20.1 0 50
GPS switch -18.1 -16.1 -14.1 0 50
Predicted Temps (°C) Operational Limits
Overall Model: Hot Case
Component
Min Ave Max Cold Hot
Batteries 48.7 49.3 50.0 5 20
Boards 26.0 29.2 37.2 -40 80
PPU 56.4 63.3 68.6 -55 125
PPT Capacitors -20.4 -6.0 13.1 N/A 125
Thrusters -20.0 -4.5 16.0 -40 100
Predicted Temps (°C) Operational Limits
Overall Model: Hot Case
Component
Min Ave Max Cold Hot
Cameras -21.2 7.3 57.8 -20 60
Rate gyros 15.6 16.7 17.9 -40 80
Magnetometer -3.1 25.3 56.4 -40 85
D/L transmitter 23.5 42.9 68.3 -20 70
U/L receiver 11.6 37.9 56.5 -20 70
Predicted Temps (°C) Operational Limits
Overall Model: Hot Case
Component
Min Ave Max Cold Hot
GPS filter -4.7 7.2 24.1 0 50
GPS isolator -14.2 -12.4 -10.5 0 50
GPS NCLT 45.4 45.5 45.7 0 50
GPS preamp -4.2 7.5 23.5 0 50
GPS switch -14.3 -12.3 -10.4 0 50
Predicted Temps (°C) Operational Limits
Parametric Study: Battery Box
Batteries
Min Ave Max Cold Hot
Hot Case 17.3 22.8 28.5 5 20
Cold Case 11.8 17.5 23.3 5 20
Predicted Temps (°C) Operational Limits
• Assumed thermal filler (h = 14000 W/m2°C) used at bolted interface between battery box frame and nadir panel
Parametric Study: Effect of h
• Assumed h = 1000 W/m2°C at all bolted interfaces
• Variance of less than ±2 °C in most component temperatures
• In general, the variance indicated that a lower value of h is conservative
Plans
• Verify G’s with CEE, battery box testing
• Study effects of MLI
• Procure interface materials (indium tape)
• Examine possibility of heater control for cold components
• Study survival and shuttle bay environments
Recap
• Thermal models
• Results from models
• Parametric studies
• Future plans
Conclusions
• Detailed thermal model of HokieSat has been generated and tested
• Additional analyses are necessary
• Verification of model with test data desired
• Some changes to the thermal design are required