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Matthew Guyon Week 5: February 15 th , 2007

Matthew Guyon Week 5: February 15 th , 2007. Thermal Control/Team Leader Mars Rover Thermal Control System/ Ablative Thermal Protection System. MR Thermal Control System. Power Number Provided by Jon Kubiak on 2-15-07. Numbers based on code on slides 10 and 11. Guyon, 2. Adhesive Bond.

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Matthew Guyon Week 5: February 15 th , 2007

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  1. Matthew GuyonWeek 5: February 15th, 2007 Thermal Control/Team Leader Mars Rover Thermal Control System/ Ablative Thermal Protection System

  2. MR Thermal Control System Power Number Provided by Jon Kubiak on 2-15-07 Numbers based on code on slides 10 and 11 Guyon, 2

  3. Adhesive Bond Honeycomb Core Adhesive Bond Composite Insulation Ablative Material Ablative Thermal Protection TC Drawing by: Ben Jamison Guyon, 3

  4. 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

  5. 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. 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 Numbers Based on Ref Slide 7 Guyon, 6

  7. Thermal Re-Entry Protection Numbers for Material, Density, Thickness, Operating Temp, Heat rejection and Total mass come from research with the references of 1-8 Guyon, 7

  8. Thermal Re-Entry Protection SODDIT Code Graphs 2-14-07 Guyon, 8

  9. Thermal Re-Entry Protection SODDIT Code Graphs 2-14-07 Guyon, 9

  10. MR Thermal Control System Ref 1: Larson Guyon, 10

  11. MR Thermal Control System Numbers from my own research and code Guyon, 11

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