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Molly Kane January 17, 2008 Interface Structures, Aero- and Thermo-Loading Nose Cone Materials

This document discusses the sizing and materials of the nose cone for the AAE 450 Spring 2008 Structures project, including options such as aluminum, titanium, magnesium alloys, molybdenum, carbon-carbon, and hafnium diboride.

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Molly Kane January 17, 2008 Interface Structures, Aero- and Thermo-Loading Nose Cone Materials

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  1. Molly KaneJanuary 17, 2008Interface Structures, Aero- and Thermo-LoadingNose Cone Materials AAE 450 Spring 2008

  2. Sizing • Size of nose cone based on historical data from Vanguard rocket • Ltotal – 12.64 m • Radius – 0.3344 m • Lnose_cone – 1.071 m • Surface Area – 1.178 m AAE 450 Spring 2008 Structures

  3. Materials • Aluminum – low heat applications, relatively inexpensive • Titanium – strong, high temperature usage • Magnesium Alloys – low density, low heat applications • Molybdenum – very high heat capabilities, maintains strength • Carbon-Carbon – ceramic, light, very expensive • Hafnium Diboride – ceramic, light, very high heat capabilities Future Work • Ceramics, combinations of materials, aero-thermal implications, pricing AAE 450 Spring 2008 Structures

  4. Backup Slides AAE 450 Spring 2008 Structures

  5. References Anonymous, “Titanium, Commercially Pure”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Anonymous, “Magnesium, Mg-6Al-1Zn”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Anonymous, “Aluminum, Al-2.5Mg-0.25Cr”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Anonymous, “Carbon-Carbon Composite Thermal Protection System for Spacecraft from NextTechs Technologies,” NextTechs Technology c. 2000-2008, [http://www.azom.com/details.asp?ArticleID=3904. Accessed 1/16/08] Buckman, R.W., “Molybdenum, Commercially Pure”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Ewig, R. Sandhu, J. Shell, C.A., Schneider, M.A., Bloom, J.B., Ohno, S., “The K2X: Design of a 2nd Generation Reusable Launch Vehicle,” 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Huntsville, AL, 2000, pp. 11-12. Klemans, B., “The Vanguard Satellite Launching Vehicle” The Martin Company, Engineering Report No. 11022, April 1960. AAE 450 Spring 2008 Structures

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