aae450 senior spacecraft design matthew guyon week 5: february 15 th, 2007 thermal control/team...
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AAE450 Senior Spacecraft Design
Matthew GuyonWeek 5: February 15th, 2007
Thermal Control/Team Leader
Mars Rover Thermal Control System/
Ablative Thermal Protection System
AAE450 Senior Spacecraft Design
MR Thermal Control System
Energy for MR using completely active system
Total Peak Power 58 kW
Total Area Needed for a Two-Sided Radiator
2.91 m2
Guyon, 2
Power Number Provided by Jon Kubiak on 2-15-07
Mass (kg) Power (kW) Volume (m3)
Coldplates 120.00 0.28
Pumps 278.40 1.33 0.99
Plumbing and Valves 90.42
Instruments and Controls 30.14
Fluids 30.14
Radiators 204.43 0.08
Total 0.75 mt 1.33 kW 1.34 m3
Numbers based on code on slides 10 and 11
AAE450 Senior Spacecraft Design
Ablative Thermal Protection
Guyon, 3
Composite Insulation
Adhesive Bond
Honeycomb Core
Adhesive Bond
Ablative Material
TC Drawing by: Ben Jamison
0 100 200 300 400 500 600 700 8000
0.5
1
1.5
2
2.5
3
3.5
4
4.5
Time (sec)
dept
h (c
m)
Avcoat.m Ablation at heating point 5 for tabl = 0.017 and tinslator = 0.02
Original Depth
Ablation DepthCarbon Carbon Foam
Graphite-Carbon skin
0 100 200 300 400 500 600 700 800 900150
200
250
300
350
400
450
500
550
600
Time (sec)
Tem
p (K
)
Avcoat.m Temperature at heating point 5 for tabl
= 0.017 and tinslator
= 0.02
Outer Layer
Between Ablator and Carbon Foam
Between Carbon Foam and Composite skin
Inside wall of ship
Max temp of inner wall
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: “Atmospheric Reentry.” 4 Jan 2007 Wikipedia. 5 Jan 2007. <http://en.wikipedia.org/wiki/Heat_shield>
• Ref 3: “Project Legend.” Spring 2005 Purdue University. 5 Jan 2007 (Pgs 163-169) <https://engineering.purdue.edu/AAE/Academics/Courses/aae450/2005/spring>
• Ref 4: “Inconel 617 Technical Data.” HighTempMetals.com. 29 Jan 2007. <http://www.hightempmetals.com/techdata/hitempInconel617data.php>
• Ref 5: “Low density ablator composition.” Freepatentsonline.com. 29 Jan 2007. <http://www.freepatentsonline.com/6627697.html>
• Ref 6: “Orbiter Thermal Protection System.” Nasa Facts Online. 30 Jan 2007. <http://www-pao.ksc.nasa.gov/kscpao/nasafact/tps.htm>
• Ref 7: “CSM Heat Shield.” Astronautix.com. 29 Jan 2007. <http://www.astronautix.com/craft/csmhield.htm>
• Ref 8: Gilmore, David G.. Spacecraft Thermal Control Handbook. California: The Aerospace Corporation
Guyon, 4
AAE450 Senior Spacecraft Design
Thermal Re-Entry Protection
• Mars Entry With Aeroshell:– Absorptive System – Charring Ablator– Char Outer Shell with a Virgin Ablator
Honeycomb Core with a Back-face bonding
– Material Based on new Technology – Boeing Lightweight Ablator (BLA)
• Mars Entry With Lifting Body:– Radiative System - Insulated– Outer Shell: Metallic – Inner Shell: Thermal Insulation – Material Based on X-33 – Inconel 617
• Earth Re-Entry:– Absorptive System – Charring Ablator– Char Outer Shell with a Virgin Ablator
Honeycomb Core with a Back-face bonding
– Material based on Apollo Spacecraft – Avco 5026-39
Figures based on Larson, Wiley and Pranke, Linda, ref 1 Guyon, 5
AAE450 Senior Spacecraft Design
Thermal Re-Entry Protection
• Mars Entry With Aeroshell:– Excellent abrasion resistance – Radio frequency transparent,
moisture resistant, and low cost
• Mars Entry With Lifting Body:– Excellent high temperature
strength– Excellent resistance to
oxidation and a wide range of corrosive elements
• Earth Re-Entry:– Well tested– Resistant to high temperatures
experienced in Earth re-entry
Mars Mars Earth
Aeroshell Lifting Body Re-entry
Material BLA Inconel 617 Avco 5026-39
Density (kg/m3) 320 8359.33 512
Thickness (m) 0.04 0.006 0.0254
Operating Temp (k)
2000 2100 3033
Heat Rejection (W/cm2)
91.18 110.80 481.40
Total Mass (kg/m2)
16.42 50.76 18.74
Guyon, 6Numbers Based on Ref Slide 7
AAE450 Senior Spacecraft Design
Thermal Re-Entry Protection
Mars Earth
Aeroshell Lifting Body Re-entry
Material BLA Inconel 617 Avco 5026-39
Density (kg/m^3) 320 8359.33 512
Thickness (m) 0.04 0.006 0.0254
Operating Temp (k) 2000 2100 3033
Heat Rejec (W/cm^2)
=(0.0000000567*C7^5)/(C7-10)/100^2
=(0.0000000567*D7^5)/(D7-10)/100^2
=(0.0000000567*E7^5)/(E7-10)/100^2
Total Mass (kg/m^2) =C5*C6+3.62 =D5*D6+0.6 =E5*E6+5.74
Guyon, 7
Numbers for Material, Density, Thickness, Operating Temp, Heat rejection and Total mass come from research with the references of 1-8
AAE450 Senior Spacecraft Design
Thermal Re-Entry Protection
0 100 200 300 400 500 600 700 8000
0.5
1
1.5
2
2.5
3
3.5
4
4.5
Time (sec)
depth
(cm
)
Avcoat.m Ablation at heating point 5 for tabl
= 0.017 and tinslator
= 0.02
Original Depth
Ablation DepthCarbon Carbon Foam
Graphite-Carbon skin
Guyon, 8SODDIT Code Graphs 2-14-07
AAE450 Senior Spacecraft Design
Thermal Re-Entry Protection
0 100 200 300 400 500 600 700 800 900150
200
250
300
350
400
450
500
550
600
Time (sec)
Tem
p (
K)
Avcoat.m Temperature at heating point 5 for tabl
= 0.017 and tinslator
= 0.02
Outer Layer
Between Ablator and Carbon Foam
Between Carbon Foam and Composite skin
Inside wall of ship
Max temp of inner wall
Guyon, 9SODDIT Code Graphs 2-14-07
AAE450 Senior Spacecraft Design
MR Thermal Control System Mass (kg) Power (kW) Volume(m3)
Heat Exchangers 17 + 0.25 * capacity in kW 00.016 + 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 02.03E-7 * capacity in W *
(length in m)2
Guyon, 10
Ref 1: Larson
AAE450 Senior Spacecraft Design
MR Thermal Control System
Guyon, 11
Energy (W) 58000.00
Condction KA(T2-T1)/(X2-X1)
k (w/mk) 237.00
thickness (m) 0.04
Convection hA(T2-T1)
h (w/m^2k) 50.00
dela T 80.00
ratiation AEST^4
Eps (Anodized Aluminum-black) 0.84
S (Stephan-Boltzmann constant) 5.67E-08
T (surface) 375.00
area (m^2) 2.91
Rho of AL (kg/m^3) 2700.00
mass (kg) 299.79
Mass (kg) Power (kW) Volume (m3)
Coldplates 120.00 0.28
Pumps 278.40 1.33 0.99
Plumbing and Valves 90.42
Instruments and Controls 30.14
Fluids 30.14
Radiators 204.43 0.08
Total 0.75 mt 1.33 kW 1.34 m3
Numbers from my own research and code