DANSK DS/CEN/CLC/TR 17603-31-16 PDF

The thermal protection system (TPS) of a space vehicle ensures the structural integrity of the surface of the craft and maintains the correct internal temperatures (for crew, electronic equipment, etc.) when the vehicle is under the severe thermal loads of re-entry. These loads are characterised by very large heat fluxes over the relatively short period of re-entry. The design of thermal protection systems for re-entry vehicles is very complex due to the number and complexity of phenomena involved: the flow around the vehicle is hypersonic, tridimensional and reactive, and its interaction with the vehicle’s surface may induce chemical reactions which are not fully understood. Two TPS concepts for re-entry vehicles, ablative and radiative are examined and there is also an anlyisis of existing systems using them. The Thermal design handbook is published in 16 Parts TR 17603-31-01 Part 1A Thermal design handbook – Part 1: View factors TR 17603-31-01 Part 2A Thermal design handbook – Part 2: Holes, Grooves and Cavities TR 17603-31-01 Part 3A Thermal design handbook – Part 3: Spacecraft Surface Temperature TR 17603-31-01 Part 4A Thermal design handbook – Part 4: Conductive Heat Transfer TR 17603-31-01 Part 5A Thermal design handbook – Part 5: Structural Materials: Metallic and Composite TR 17603-31-01 Part 6A Thermal design handbook – Part 6: Thermal Control Surfaces TR 17603-31-01 Part 7A Thermal design handbook – Part 7: Insulations TR 17603-31-01 Part 8A Thermal design handbook – Part 8: Heat Pipes TR 17603-31-01 Part 9A Thermal design handbook – Part 9: Radiators TR 17603-31-01 Part 10A Thermal design handbook – Part 10: Phase – Change Capacitors TR 17603-31-01 Part 11A Thermal design handbook – Part 11: Electrical Heating TR 17603-31-01 Part 12A Thermal design handbook – Part 12: Louvers TR 17603-31-01 Part 13A Thermal design handbook – Part 13: Fluid Loops TR 17603-31-01 Part 14A Thermal design handbook – Part 14: Cry ...