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AAE450 Senior Spacecraft Design Matthew Guyon Week 5: February 15 th, 2007 Thermal Control/Team Leader Mars Rover Thermal Control System/ Ablative Thermal.

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Presentation on theme: "AAE450 Senior Spacecraft Design Matthew Guyon Week 5: February 15 th, 2007 Thermal Control/Team Leader Mars Rover Thermal Control System/ Ablative Thermal."— Presentation transcript:

1 AAE450 Senior Spacecraft Design Matthew Guyon Week 5: February 15 th, 2007 Thermal Control/Team Leader Mars Rover Thermal Control System/ Ablative Thermal Protection System

2 AAE450 Senior Spacecraft Design MR Thermal Control System Energy for MR using completely active system Total Peak Power58 kW Total Area Needed for a Two-Sided Radiator2.91 m 2 Guyon, 2 Power Number Provided by Jon Kubiak on 2-15-07 Mass (kg)Power (kW)Volume (m 3 ) Coldplates120.00 0.28 Pumps278.401.330.99 Plumbing and Valves90.42 Instruments and Controls30.14 Fluids30.14 Radiators204.43 0.08 Total 0.75 mt1.33 kW1.34 m 3 Numbers based on code on slides 10 and 11

3 AAE450 Senior Spacecraft Design Ablative Thermal Protection Guyon, 3 Composite Insulation Adhesive Bond Honeycomb Core Adhesive Bond Ablative Material TC Drawing by: Ben Jamison

4 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. Ref 3: “Project Legend.” Spring 2005 Purdue University. 5 Jan 2007 (Pgs 163-169) Ref 4: “Inconel 617 Technical Data.” HighTempMetals.com. 29 Jan 2007. Ref 5: “Low density ablator composition.” Freepatentsonline.com. 29 Jan 2007. Ref 6: “Orbiter Thermal Protection System.” Nasa Facts Online. 30 Jan 2007. Ref 7: “CSM Heat Shield.” Astronautix.com. 29 Jan 2007. Ref 8: Gilmore, David G.. Spacecraft Thermal Control Handbook. California: The Aerospace Corporation Guyon, 4

5 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

6 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 Earth AeroshellLifting BodyRe-entry MaterialBLAInconel 617Avco 5026-39 Density (kg/m 3 )3208359.33512 Thickness (m)0.040.0060.0254 Operating Temp (k) 200021003033 Heat Rejection (W/cm 2 ) 91.18110.80481.40 Total Mass (kg/m 2 ) 16.4250.7618.74 Guyon, 6 Numbers Based on Ref Slide 7

7 AAE450 Senior Spacecraft Design Thermal Re-Entry Protection Mars Earth AeroshellLifting BodyRe-entry MaterialBLAInconel 617Avco 5026-39 Density (kg/m^3)3208359.33512 Thickness (m)0.040.0060.0254 Operating Temp (k)200021003033 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

8 AAE450 Senior Spacecraft Design Thermal Re-Entry Protection Guyon, 8 SODDIT Code Graphs 2-14-07

9 AAE450 Senior Spacecraft Design Thermal Re-Entry Protection Guyon, 9 SODDIT Code Graphs 2-14-07

10 AAE450 Senior Spacecraft Design MR Thermal Control System Mass (kg)Power (kW)Volume(m 3 ) Heat Exchangers17 + 0.25 * capacity in kW0 0.016 + 0.0012 * capacity in kW Coldplates12 * capacity in kW00.028 * capacity in kW Pumps with Accumulator4.8 * loop capacity in kW 0.023 * loop capacity in kW0.017 * loop capacity in kW Plumbing and ValvesAdd 15% to active systemNegligible Instruments and ControlsAdd 5% to active systemNegligible FluidsAdd 5% to active system0Negligible Heat Pumps8 * capacity in kWVariesNegligible Fixed Radiators5.3 per m 2 Negligible0.02 per m 2 MLI1-3 per m 2 Negligible0.01 per m 2 Heat Pipes0.000294 * capacity in W * (length in m) 2 0 2.03E-7 * capacity in W * (length in m) 2 Guyon, 10 Ref 1: Larson

11 AAE450 Senior Spacecraft Design MR Thermal Control System Guyon, 11 Energy (W)58000.00 CondctionKA(T2-T1)/(X2-X1) k (w/mk)237.00 thickness (m)0.04 ConvectionhA(T2-T1) h (w/m^2k)50.00 dela T80.00 ratiationAEST^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 (m 3 ) Coldplates120.00 0.28 Pumps278.401.330.99 Plumbing and Valves90.42 Instruments and Controls30.14 Fluids30.14 Radiators204.43 0.08 Total0.75 mt1.33 kW1.34 m 3 Numbers from my own research and code

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