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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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Presentation on theme: "AAE450 Senior Spacecraft Design Rick Hutchings Week 8: March 8 th, 2007 Thermal Control Insulation and COM Sat Thermal Control."— Presentation transcript:

1 AAE450 Senior Spacecraft Design Rick Hutchings Week 8: March 8 th, 2007 Thermal Control Insulation and COM Sat Thermal Control

2 AAE450 Senior Spacecraft Design COM Sat Thermal Control Mass (kg) Power (kW) Volume(m 3 ) Heaters3.50 0.24 Pump24.00.120.17 Plumbing and Valves41.4 Instruments and Controls13.8 Fluids13.8 Radiators248 0.00 MLI41.41 0.41 Total386.5 0.120.82 Total (mt) 0.387 Rick Hutchings - 2 Mars Sat Q = 5kW Mass (kg) Power (kW) Volume(m 3 ) Heaters0.35 0.24 Pumps2.400.010.02 Plumbing and Valves4.14 Instruments and Controls1.38 Fluids1.38 Radiators24.85 0.00 MLI41.41 0.00 Total75.91 0.010.26 Total (mt) 0.0759 Gangale Sat Q = 20 kW

3 AAE450 Senior Spacecraft Design Tank Insulation Thickness Rick Hutchings - 3 MLI for LOX and LH2 tanks Spray on Foam for External Tanks Mass (mt)Volume(m^3) ET0.85423.48 MT0.64517.75 dE2.97192.84 LOX Pipe0.81822.51 LH2 Pipe0.95126.16 ISPP LOX1.80949.76 ISPP LH23.16286.97

4 AAE450 Senior Spacecraft Design References 1)Fischer, Mark. Thermal Control. Feb 1995. University of Texas. 21 Jan 2007. 2)Larson, Wiley and Pranke, Linda. Human Spaceflight Mission Analysis and Design. St. Louis: McGraw-Hill Companies (Pg. 513-537) 3)“Project Legend.” Spring 2005 Purdue University. 5 Jan 2007 (Pg. 285 289) <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

5 AAE450 Senior Spacecraft Design Back-up Slides Mass (kg)Power (kW)Volume(m 3 ) Heat Exchangers 17 + 0.25 * capacity in kW0 0.016 + 0.0012 * capacity in kW Coldplates12 * capacity in kW00.028 * capacity in kW Pumps with Accumulator 4.8 * loop capacity in kW0.023 * loop capacity in kW0.017 * loop capacity in kW Plumbing and Valves Add 15% to active systemNegligible Instruments and Controls Add 5% to active systemNegligible Fluids Add 5% to active system0Negligible Heat Pumps8 * capacity in kWVariesNegligible Fixed Radiators5.3 per m 2 Negligible0.02 per m 2 From Table 16-7 in Larson, Wiley, and Pranke, Linda, ref. 2 Rick Hutchings - 5

6 AAE450 Senior Spacecraft Design A = Q/ q q: heat rejection rate(W/m 2 ) Q: heat load = ((52.5 – 15.448)*1000)/171 =216.678m 2 Rick Hutchings - 6

7 AAE450 Senior Spacecraft Design Heat Rejection Q = es AT 4 = 0.75*5.67e-8*207.345*(249.2) 4 = 34 kW Rick Hutchings - 7

8 AAE450 Senior Spacecraft Design Heat Rejection for MLI Rick Hutchings - 8

9 AAE450 Senior Spacecraft Design Updated Numbers VehicleMass (mt)Power (kW)Volume (m^3) TV2.790.8213.51 TC0.3280.031.4 Rick Hutchings - 9

10 AAE450 Senior Spacecraft Design Insulation Rick Hutchings - 10 ET Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W) LOX0.1875545.1582480.0351279110.111 LH20.52057814.3173150.0478164329.6777 Ext Tank0.1457294.0079580.01518827 Total0.85386123.483521 39.7887 MT Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W) LOX0.1546114.2522360.0351278812.276 LH20.3473689.5535820.0478164350.229 Ext Tank0.1434053.9440290.02425152 Total0.64538417.749847 62.505

11 AAE450 Senior Spacecraft Design dE Insulation Rick Hutchings - 11 dE Mass (mt)Volume (m^3)Thickness (m)Heat Loss (W) LOX0.54688117.0900260.0342214141.68 LH21.21040237.8250720.04690994122.97 Ext Tank1.21367737.927420.03784669 Total2.9709692.842518 164.65

12 AAE450 Senior Spacecraft Design ISPP Insulation Rick Hutchings - 12 ISPP LOX Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W) LOX Tank1.57054343.194250.03512784173.0213 Ext Tank0.2386676.5640110.0151885 Total1.8092149.758261 173.0213 ISPP LH2 Mass (mt)Volume (m^3)Thickness (m)Heat Loss (W) LH2 Tank2.72212674.865960.04781639240.69 Ext Tank0.43997512.1005280.01518869 Total3.16210186.966488 240.69

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