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Matthew Guyon Week 3: February 1 st , 2007

Matthew Guyon Week 3: February 1 st , 2007. Thermal Control/Team Leader Thermal Re-Entry Protection Systems / TV Thermal Control System. TV Thermal Control System. Numbers for Thermal Control Created by Rick Huchings. Thermal Re-Entry Protection. Mars Entry With Aeroshell:

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Matthew Guyon Week 3: February 1 st , 2007

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  1. Matthew GuyonWeek 3: February 1st, 2007 Thermal Control/Team Leader Thermal Re-Entry Protection Systems / TV Thermal Control System

  2. TV Thermal Control System Numbers for Thermal Control Created by Rick Huchings

  3. 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

  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

  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

  6. Thermal Re-Entry Protection

  7. TV Thermal Control System

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