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

CONTENTS

1. DESCRIPTION

2. TRANSLATION

3. FORMULATION

4. SELECTION

5. SUPPORTING INFORMATION

6. COMMENTS

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

SPACE SHUTTLE ORBITER

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

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

SELECTION

CONTD…

CONTD…

CONTD…

RANKING

1. Nylon

2. Silicone rubber

3. Ceramics

SUPPORTING INFORMATION

• Nylon material coated with silicone elastomer

• Bonded to aluminum sheets by RTV silicone adhesives

• Thickness of blanket – 4 & 8 mm

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