1. AAE 450 Spring 2008 Vince Teixeira 24 January 2008 Structures Nose Cone Structural/Material Analysis 1

2. AAE 450 Spring 2008 Structures Thermal Analysis  0.70 Power-Law Body  Standard Atmosphere Table/Isentropic Mach Flow  Preliminary T melt Analysis –Al:964 m/s –Mg:1029 m/s –Ti:1833 m/s –Austenitic Steel:1688 m/s –Martensitic Steel:1729 m/s –Ultra High Strength Steel: 1774 m/s –HfB 2 2627 m/s 2

3. AAE 450 Spring 2008 Structures Mass Estimate  Linear Scaling for 5kg Vanguard rocket (Strauss, Chris)  82 cm Diameter, 164 cm Length, 2 cm thick –Al:159.27 kg –Mg:99.12 kg –Ti:262.30 kg –Austenitic Steel:453.11kg –Martensitic Steel:447.30 kg –Ultra High Strength Steel:451.21 kg Future Work  Specific Aerothermal load analysis (w/ CAD)  Manufacturing Costs 3

4. Backup Slide – Power-Law Body AAE 450 Spring 2008 Structures 4

5. Backup Slide – Thermal Analysis AAE 450 Spring 20085

6. References  Auman, Lamar M. and Wilks, Brett, “Supersonic and Hypersonic Minimum Drag for Bodies of Revolution.” AIAA 2003-3417, Orlando, FL, June 2003.  Santos, W. F. N., “Leading Edge Bluntness Effects on Aerodynamic Heating and Drag of Power Law Body in Low-Density Hypersonic Flow,” AIAA Journal, Vol. XXVII, No. 3, 2005, pp. 236-242.  Aerospace Structural Metals Handbook, 2000 Edition AAE 450 Spring 2008 Structures 6