AAE450 Senior Spacecraft Design Rick Hutchings Week 8: March 8 th, 2007 Thermal Control Insulation...
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AAE450 Senior Spacecraft Design Rick Hutchings Week 8: March 8 th , 2007 Thermal Control Insulation and COM Sat Thermal Control
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Transcript of AAE450 Senior Spacecraft Design Rick Hutchings Week 8: March 8 th, 2007 Thermal Control Insulation...
AAE450 Senior Spacecraft Design
Rick HutchingsWeek 8: March 8th, 2007
Thermal Control
Insulation and COM Sat Thermal Control
AAE450 Senior Spacecraft Design
COM SatThermal Control
Mass
(kg)Power
(kW)Volume(
m3)
Heaters 3.50 0.24
Pump 24.0 0.12 0.17
Plumbing and Valves 41.4
Instruments and Controls 13.8
Fluids 13.8
Radiators 248 0.00
MLI 41.41 0.41
Total 386.5 0.12 0.82
Total (mt) 0.387
Rick Hutchings - 2
Mars Sat
Q = 5kW
Mass (kg)
Power (kW)
Volume(m3)
Heaters 0.35 0.24
Pumps 2.40 0.01 0.02
Plumbing and Valves 4.14
Instruments and Controls 1.38
Fluids 1.38
Radiators 24.85 0.00
MLI 41.41 0.00
Total 75.91 0.01 0.26
Total (mt) 0.0759
Gangale Sat
Q = 20 kW
AAE450 Senior Spacecraft Design
Tank Insulation Thickness
Rick Hutchings - 3
MLI for LOX and LH2 tanksSpray on Foam for External Tanks
Mass (mt) Volume(m^3)
ET 0.854 23.48
MT 0.645 17.75
dE 2.971 92.84
LOX Pipe 0.818 22.51
LH2 Pipe 0.951 26.16
ISPP LOX 1.809 49.76
ISPP LH2 3.162 86.97
AAE450 Senior Spacecraft Design
References
1) Fischer, Mark. Thermal Control. Feb 1995. University of Texas. 21 Jan2007. <http://www.tsgc.utexas.edu/archive/subsystems/thermal.pdf>
2) Larson, Wiley and Pranke, Linda. Human Spaceflight Mission Analysisand Design. St. Louis: McGraw-Hill Companies (Pg. 513-537)
3) “Project Legend.” Spring 2005 Purdue University. 5 Jan 2007 (Pg. 285289) <https://engineering.purdue.edu/AAE/Academics/Courses/aae450/2005/spring>
4) Gilmore, David G. Spacecraft Thermal Control Handbook. California: The Aerospace Corporation
5) Martin, J.J. and Hastings, L. Large-Scale Liquid Hydrogen Testing of a Variable Density Multilayer Insulation with a Foam Substrate. June 2001. NASA
6) NASA Facts. External Tank Return to Flight Focus Area Thermal Protection System. August 2004.
Rick Hutchings - 4
AAE450 Senior Spacecraft Design
Back-up Slides Mass (kg) Power (kW) Volume(m3)
Heat Exchangers17 + 0.25 * capacity in
kW 00.016 + 0.0012 * capacity in
kW
Coldplates 12 * capacity in kW 0 0.028 * capacity in kW
Pumps withAccumulator
4.8 * loop capacity in kW 0.023 * loop capacity in kW 0.017 * loop capacity in kW
Plumbing andValves
Add 15% to active system Negligible Negligible
Instruments andControls
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
From Table 16-7 in Larson, Wiley, and Pranke, Linda, ref. 2
Rick Hutchings - 5
AAE450 Senior Spacecraft Design
A = Q/qq: heat rejection rate(W/m2)Q: heat load= ((52.5 – 15.448)*1000)/171=216.678m2
Rick Hutchings - 6
AAE450 Senior Spacecraft Design
Heat Rejection
• Q = esAT4
= 0.75*5.67e-8*207.345*(249.2)4
= 34 kW
Rick Hutchings - 7
AAE450 Senior Spacecraft Design
Heat Rejection for MLI
8 2.6 10 4.67 4.67 1.88.95 10 15 5.39 10 0.031
2hot liq
MLI hot liq hot liq
T TQ T T T T
layers
Rick Hutchings - 8
AAE450 Senior Spacecraft Design
Updated Numbers
Vehicle Mass (mt) Power (kW) Volume (m^3)
TV 2.79 0.82 13.51
TC 0.328 0.03 1.4
Rick Hutchings - 9
AAE450 Senior Spacecraft Design
Insulation
Rick Hutchings - 10
ETMass (mt)
Volume (m^3)
Thickness (m)
Heat Loss (W)
LOX 0.187554 5.158248 0.03512791 10.111
LH2 0.520578 14.317315 0.04781643 29.6777
Ext Tank 0.145729 4.007958 0.01518827
Total 0.853861 23.483521 39.7887
MTMass (mt)
Volume (m^3)
Thickness (m)
Heat Loss (W)
LOX 0.154611 4.252236 0.03512788 12.276
LH2 0.347368 9.553582 0.04781643 50.229
Ext Tank 0.143405 3.944029 0.02425152
Total 0.645384 17.749847 62.505
AAE450 Senior Spacecraft Design
dE Insulation
Rick Hutchings - 11
dE Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W)
LOX 0.546881 17.090026 0.03422141 41.68
LH2 1.210402 37.825072 0.04690994 122.97
Ext Tank 1.213677 37.92742 0.03784669
Total 2.97096 92.842518 164.65
AAE450 Senior Spacecraft Design
ISPP Insulation
Rick Hutchings - 12
ISPP LOX
Mass (mt)
Volume (m^3)
Thickness (m)
Heat Loss (W)
LOX Tank 1.570543 43.19425 0.03512784 173.0213
Ext Tank 0.238667 6.564011 0.0151885
Total 1.80921 49.758261 173.0213
ISPP LH2 Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W)
LH2 Tank 2.722126 74.86596 0.04781639 240.69
Ext Tank 0.439975 12.100528 0.01518869
Total 3.162101 86.966488 240.69
