AAE450 Senior Spacecraft Design
Matthew Guyon
Week 7: March 1st, 2007
Thermal Control Group/Team Leader
Manned Rover TCS/
Mars Crawler TCS/
Sample Return TCS
AAE450 Senior Spacecraft Design
MR Thermal Control System
Power Number Provided by Jon Kubiak on 2-15-07
TCS for MR created by Matthew Guyon, last modified on 2-28-07
Numbers based on equation on slide 8 and attached code on pages 9-15
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AAE450 Senior Spacecraft Design
MR Thermal Control System
TCS for SR created by Matthew Guyon,
last modified on 2-28-07
TCS for MC created by Matthew Guyon,
last modified on 2-28-07
Power Number Provided by Courtney Rogge on 2-23-07
Power Number Provided by Courtney Rogge on 2-23-07 of
300 kW and modified by Steve Kassab with 90% efficiency
to bring it to 30 kW total heat rejected
Numbers for both sets based on equation on slide 8 and attached code on pages 9-15
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AAE450 Senior Spacecraft Design
References
•
Ref 1: Larson, Wiley and Pranke, Linda. Human Spaceflight Mission Analysis and Design. St.
Louis: McGraw-Hill Companies (Pgs 513-537)
•
Ref 2: Incropera, Frank P., DeWitt, David P. Fundamentals of Heat and Mass Transfer Fourth
Edition. New York: John Wiley and Sons 1996
•
Ref 3: Gilmore, David G.. Spacecraft Thermal Control Handbook. California: The Aerospace
Corporation
•
Ref 4: “Heat Transfer.” 25 Feb 2007 Wikibooks. 25 Feb 2007.
<http://en.wikibooks.org/wiki/Heat_Transfer#Convection>
•
Ref 5: “Heat Transfer Coefficients .” 25 Feb. 2007 The Engineering Toolbox. 25 Feb 2007
<http://www.engineeringtoolbox.com/heat-transfer-coefficients-exchangers-d_450.html>
•
Ref 6: “Material Emissivity Properties.” Electro-optical.com. 25 Feb 2007.
<http://www.electro-optical.com/bb_rad/emissivity/matlemisivty.htm>
•
Ref 7: “Convection.” Knowledgerush.com. 25 Feb 2007.
<http://www.knowledgerush.com/kr/encyclopedia/Convection>
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AAE450 Senior Spacecraft Design
MR Thermal Control System
Mass (kg)
Power (kW)
Volume(m3)
Heat Exchangers
17 + 0.25 * capacity in kW
0
0.016 + 0.0012 * capacity in
kW
Coldplates
12 * capacity in kW
0
0.028 * capacity in kW
Pumps with
Accumulator
4.8 * loop capacity in kW
0.023 * loop capacity
in kW
0.017 * loop capacity in kW
Plumbing and
Valves
Add 15% to active system
Negligible
Negligible
Instruments and
Controls
Add 5% to active system
Negligible
Negligible
Fluids
Add 5% to active system
0
Negligible
Heat Pumps
8 * capacity in kW
Varies
Negligible
Fixed Radiators
5.3 per m2
Negligible
0.02 per m2
MLI
1-3 per m2
Negligible
0.01 per m2
Heat Pipes
0.000294 * capacity in W * (length in m)2
0
2.03E-7 * capacity in W *
(length in m)2
Larson1
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AAE450 Senior Spacecraft Design
Convection
• Q = hA(T2-T1)
• h = 50.00; (w/m^2-k) for al
• Value for h for
aluminum is based
on Heat Transfer
Coefficients5
• Picture based on
drawling from
Convection7
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AAE450 Senior Spacecraft Design
Radiation
• Q = CAES(T2-T1)^4
• E = 0.84; for Anodized Aluminum-black
• S = 5.67e-08; Stephan-Boltzmann
constant
• Constant for emissivity for aluminum is
based on Material Emissivity Properties6
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AAE450 Senior Spacecraft Design
Solving for Area
• A = Q/(K*h*(t_ref - t_in) + C*E*S*(t_ref t_in)^4);
• This solves for the area needed to get rid
of the heat based on the convection and
radiation equations
• The thought for these radiators is similar to
that of a car radiator
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