Intial TPS Design - Initial Material comparison for capsule...

Info iconThis preview shows pages 1–2. Sign up to view the full content.

View Full Document Right Arrow Icon
Initial Material comparison for capsule heat shield design By Ez A Hassan Introduction: Thermal protection systems or TPS are designed for space crafts and space capsules to protect it from the heat of reentry. During reentry space vehicles are moving at very high speeds, and are encountering extreme heating conditions. Temperatures during reentry are on the order of thousands degrees Fahrenheit. There are mainly two classes of TPS, reusable TPS, and ablative TPS. Reusable Vs. ablative Reusable TPS heating results in a significant amount of energy being re-radiated from the heated surface while the rest is conducted to the TPS material. The coating for material usually has high emissivity to maximize amount of energy being radiated, and low surface catalycity to minimize convective heating. The primary material for reusable TPS is usually inorganic with low thermal conductivity to minimize the mass of the material being used Figure 1 shows the common structure for reusable TPS. Ablative TPS accommodate high heating rates and heat loads through phase change and
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Image of page 2
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 10/22/2011 for the course EAS 4710 taught by Professor Staff during the Spring '08 term at University of Florida.

Page1 / 4

Intial TPS Design - Initial Material comparison for capsule...

This preview shows document pages 1 - 2. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online