AAE450 Senior Spacecraft Design
Matthew Guyon
Week 9: March 22nd, 2007
Thermal Control Group/Group Leader
Mars Nuclear Reactor TCS/
Space Nuclear Reactor TCS
AAE450 Senior Spacecraft Design
Mars Nuclear Reactor TCS
TCS for MNR created by Matthew Guyon, last modified on 3-08-07
Radiator Area:
168.24 m2
Total Mass:
5.39 mt
Power Number of 750 kW with a 24% efficiency provided
by Mike Kowalkowskion on week 8 – 3/08/07
Numbers based on equation on slide 8 and attached code on pages 10-19
Guyon, 2
AAE450 Senior Spacecraft Design
Space Nuclear Reactor TCS
Electrical Power vs. Area of Radiator for Nuclear Power in Space
3500
3000
Electrical Power vs. Total Mass for Nuclear Power in Space
40
35
2000
30
1500
Total Mass (mt)
Area of Radiator (m2)
2500
1000
500
0
500
1000
1500
2000
2500
3000
Power (kW)
3500
4000
4500
5000
TCS for MNR created by Matthew Guyon, last modified on 3-08-07
Power Number of 500 kW to 5 MW with a 24% efficiency
Data for the space reactor in 100 kW
increments is provided on page 9
25
20
15
10
5
0
500
1000
1500
2000
2500
3000
Power (kW)
3500
4000
4500
5000
TCS for MNR created by Matthew Guyon, last modified on 3-08-07
Power Number of 500 kW to 5 MW with a 24% efficiency
Numbers based on equation on slide 8 and attached code on pages 10-19
Guyon, 3
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>
Guyon, 4
AAE450 Senior Spacecraft Design
Nuclear Reactor TCS
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
Guyon, 5
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
Guyon, 6
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
Guyon, 7
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
Guyon, 8