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MATERIAL SELECTION CASE STUDY FELT REUSABLE SURFACE INSULATION (FRSI) OF SPACE SHUTTLE ORBITER
- 1. MATERIAL SELECTION CASE STUDY FELT REUSABLE SURFACE INSULATION (FRSI) OF SPACE SHUTTLE ORBITER P R E S E N T E D B Y B A G G I O J O S E R O L L N O : 1 3 M D 0 1
- 2. CONTENTS 1. DESCRIPTION 2. TRANSLATION 3. FORMULATION 4. SELECTION 5. SUPPORTING INFORMATION 6. COMMENTS
- 3. DESCRIPTION • SPACE SHUTTLE ORBITER carries rocket • It is reusable • Subjected to high temperature(400 c) • Subjected vibration (high speed motion) • Aerodynamically smooth surface • Low density • Thermal fatigue
- 5. TRANSLATION FUNCTION == Thermal protection for space shuttle orbiter CONSTRAINTS == service temperature stiffness surface roughness OBJECTIVES == minimum weight low thermal expansion durability FREE VARIABLES == material cost
- 6. FORMULATION MATERIAL INDICES 1. Service temperature (>400) 2. High stiffness M2 = E1/2 / ρ 3. Thermal expansion coefficient M3= α / E 4. Fracture toughness M4 = σf / ρ
- 7. SELECTION
- 8. CONTD…
- 9. CONTD…
- 10. CONTD…
- 11. RANKING 1. Nylon 2. Silicone rubber 3. Ceramics
- 12. SUPPORTING INFORMATION • Nylon material coated with silicone elastomer • Bonded to aluminum sheets by RTV silicone adhesives • Thickness of blanket – 4 & 8 mm
- 13. COMMENTS • Ceramic tiles are used when temperature variation is more . • Quartz , borosilicate glass are other options • Composites with low density silica fibers are the new materials