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 transcript:

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

AAE450 Senior Spacecraft Design COM Sat Thermal Control Mass (kg) Power (kW) Volume(m 3 ) Heaters Pump Plumbing and Valves41.4 Instruments and Controls13.8 Fluids13.8 Radiators MLI Total Total (mt) Rick Hutchings - 2 Mars Sat Q = 5kW Mass (kg) Power (kW) Volume(m 3 ) Heaters Pumps Plumbing and Valves4.14 Instruments and Controls1.38 Fluids1.38 Radiators MLI Total Total (mt) Gangale Sat Q = 20 kW

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) ET MT dE LOX Pipe LH2 Pipe ISPP LOX ISPP LH

AAE450 Senior Spacecraft Design References 1)Fischer, Mark. Thermal Control. Feb University of Texas. 21 Jan )Larson, Wiley and Pranke, Linda. Human Spaceflight Mission Analysis and Design. St. Louis: McGraw-Hill Companies (Pg ) 3)“Project Legend.” Spring 2005 Purdue University. 5 Jan 2007 (Pg ) < 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 NASA 6)NASA Facts. External Tank Return to Flight Focus Area Thermal Protection System. August Rick Hutchings - 4

AAE450 Senior Spacecraft Design Back-up Slides Mass (kg)Power (kW)Volume(m 3 ) Heat Exchangers * capacity in kW * capacity in kW Coldplates12 * capacity in kW * 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

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

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

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

AAE450 Senior Spacecraft Design Updated Numbers VehicleMass (mt)Power (kW)Volume (m^3) TV TC Rick Hutchings - 9

AAE450 Senior Spacecraft Design Insulation Rick Hutchings - 10 ET Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W) LOX LH Ext Tank Total MT Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W) LOX LH Ext Tank Total

AAE450 Senior Spacecraft Design dE Insulation Rick Hutchings - 11 dE Mass (mt)Volume (m^3)Thickness (m)Heat Loss (W) LOX LH Ext Tank Total

AAE450 Senior Spacecraft Design ISPP Insulation Rick Hutchings - 12 ISPP LOX Mass (mt) Volume (m^3) Thickness (m) Heat Loss (W) LOX Tank Ext Tank Total ISPP LH2 Mass (mt)Volume (m^3)Thickness (m)Heat Loss (W) LH2 Tank Ext Tank Total