1. | EXECUTIVE SUMMARY |
1.1. | Thermal Protection Systems - Introduction |
1.2. | The Space Industry is Changing |
1.3. | Commercial Orbital Launches Growing Rapidly |
1.4. | Reusable Entry/Transfer Vehicles - Cargo and Crewed |
1.5. | LEO Partially Reusable Return Vehicle Testing Timeline |
1.6. | Thermal Protection Systems & 'Aerobraking' |
1.7. | Options for Decelerating |
1.8. | Peak Heat, Total Heat, and Stagnation Pressure |
1.9. | Categories of Thermal Protection System |
1.10. | TPS Performance Envelope (1) |
1.11. | TPS Performance Envelope |
1.12. | Role of Industry in Material and Manufacturing of Heat Shields |
1.13. | Forecasting Overview |
1.14. | Annual Installation Area of Thermal Protection Systems |
1.15. | Market Value of TPS, 1991-2035 |
1.16. | TPS Market Value Forecast (1) |
1.17. | TPS Market Value Forecast (2) |
2. | SPACE INDUSTRY |
2.1. | Thermal Protection Systems - Introduction |
2.2. | The Space Industry is Changing |
2.3. | Commercial Interest in Space |
2.4. | Commercial Orbital Launches Growing Rapidly |
2.5. | Orbital Launches by Country of Operator, 1957-2024 |
2.6. | BEO Launches Remain Low |
2.7. | SpaceX a Dominant Player Among Launch Providers |
2.8. | Space Mission Domain |
2.9. | Microgravity manufacturing |
2.10. | Commercialization of Space - Implications for Material Design |
2.11. | Cargo and Crew Capsules - TPS Enables Reusability |
2.12. | Cargo and Crew Transportation |
2.13. | Reusable Entry/Transfer Vehicles - Cargo and Crewed |
2.14. | Reusable Entry/Transfer Vehicles - Cargo and Crewed |
2.15. | LEO Partially Reusable Return Vehicle Testing Timeline |
2.16. | Partial Reusability |
2.17. | Partial Reusability - TPS Options |
2.18. | Crew/Cargo Return Vehicles |
3. | ATMOSPHERIC RE-ENTRY |
3.1. | Tsiolkovsky's Rocket Equation |
3.2. | Thermal Protection Systems & 'Aerobraking' |
3.3. | Atmospheric Entry - Overview |
3.4. | Energy of Orbital Vehicles |
3.5. | Options for Decelerating |
3.6. | Blunt Body Concept |
3.7. | Convective vs Radiative Heat |
3.8. | Peak Heat, Total Heat, and Stagnation Pressure |
3.9. | Categories of TPS |
3.10. | Categories of Thermal Protection System |
3.11. | Thermal Protection Systems |
3.12. | Cost and Performance |
3.13. | TPS Peak Heating and Pressure Limits |
3.14. | TPS Performance Envelope (1) |
3.15. | TPS Performance Envelope (2) |
3.16. | Role of Industry in Material and Manufacturing of Heat Shields |
4. | TILE-BASED TPS |
4.1. | Reusable TPS Overview |
4.2. | Material Requirements for Reusable TPS |
4.3. | Importance of Surface Emissivity |
4.4. | Thermal Conductivity |
4.5. | Temperature and Density |
4.6. | Reusable TPS Material Development Pathway |
4.7. | Spacecraft Geometry Affects Heating |
4.8. | Silica Based Tiles |
4.9. | Reinforced Carbon-Carbon (RCC) - (1) |
4.10. | Reinforced Carbon-Carbon (RCC) - (2) |
4.11. | RCC/ACC Manufacturing Overview |
4.12. | TUFROC |
4.13. | Advanced TUFROC |
4.14. | NASA Space Shuttle Orbiter vs SpaceX Starship |
4.15. | SpaceX Starship TPS |
4.16. | Thermal Conductivity and Density of Reusable TPS |
4.17. | Temperature Limits and Material Densities |
4.18. | Emissivity of TPS |
4.19. | TPS Component Manufacturers |
5. | EXPANDABLE AERODYNAMIC DECELERATORS |
5.1. | Overview |
5.1.1. | Expandable Aerodynamic Decelerators |
5.1.2. | Opportunities Enabled by EADs |
5.1.3. | Challenges for EADs |
5.1.4. | The Ballistic Coefficient |
5.1.5. | Ballistic Coefficient - Impact on Heat Flux |
5.1.6. | Venus Missions - Ballistic Coefficient and Peak Heating |
5.1.7. | Diameter on Heating |
5.1.8. | Options for Increasing the Ballistic Coefficient |
5.2. | HIAD |
5.2.1. | HIAD Deployment |
5.2.2. | NASA HIAD Construction |
5.2.3. | Material Selection for F-TPS |
5.2.4. | F-TPS |
5.2.5. | F-TPS Temperature |
5.2.6. | Aerogels for F-TPS |
5.2.7. | Gas-Generators |
5.2.8. | ATMOS PHOENIX - Commercial IAD |
5.2.9. | Booster Reusability |
5.2.10. | ULA Vulcan BE-4 Reusability |
5.3. | MDAD |
5.3.1. | NASA ADEPT |
5.3.2. | ADEPT Construction - Spiderweave |
5.3.3. | Commercial MDADs |
6. | ABLATIVE TPS |
6.1. | Overview |
6.1.1. | Ablative TPS |
6.1.2. | Ablation Introduction |
6.1.3. | High Energy Heatshield Environment |
6.1.4. | Surface Ablation Mechanisms |
6.1.5. | Pyrolysis |
6.1.6. | Material Requirements for Ablative Systems |
6.1.7. | Summary of Ablator Families(1) |
6.1.8. | Summary of Ablator Families (2) |
6.1.9. | Ablative TPS Timeline |
6.1.10. | Ablative Materials - Categorization by Form |
6.1.11. | Families of Ablators |
6.1.12. | NASA TPS Portfolio Development |
6.2. | Honeycomb Ablators |
6.2.1. | Material Composition of an Ablator (1) |
6.2.2. | Material Composition of an Ablator (2) |
6.2.3. | Honeycomb Ablators |
6.2.4. | Avcoat - Apollo to Orion |
6.2.5. | Orion Switch to Tiled Avcoat |
6.2.6. | Compositions of Silicone Ablators |
6.3. | PICA |
6.3.1. | PICA |
6.3.2. | PICA Production |
6.3.3. | PICA-X for SpaceX Dragon |
6.3.4. | Reusability of Ablators |
6.4. | Carbon Phenolic |
6.4.1. | Carbon Phenolic |
6.5. | 3D Woven TPS |
6.5.1. | Woven Thermal Protection Systems |
6.5.2. | HEEET |
6.5.3. | Woven TPS Range of Densities |
6.5.4. | Woven TPS Performance Envelope |
6.5.5. | Woven TPS for Compression Pads on Orion |
7. | FORECASTS |
7.1. | Forecasting Overview |
7.2. | Cost per kg to Orbit |
7.3. | TPS Cost Progression (1) |
7.4. | TPS Cost Progression (2) - Ablative |
7.5. | TPS Cost Progression (3) - Tile-Based |
7.6. | TPS Cost Progression (3) - Tile-Based |
7.7. | Number of Flights, 1991-2024 |
7.8. | SpaceX a Dominant Player Among Launch Providers |
7.9. | Annual Installation Area of Thermal Protection Systems |
7.10. | Market Value of TPS, 1991-2035 |
7.11. | TPS Market Value Forecast (1) |
7.12. | TPS Market Value Forecast (2) |