scope:

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 Thermal design handbook - Part 1: View factors

TR 17603-31-02 Thermal design handbook - Part 2: Holes, Grooves and Cavities

TR 17603-31-03 Thermal design handbook - Part 3: Spacecraft Surface Temperature

TR 17603-31-04 Thermal design handbook - Part 4: Conductive Heat Transfer

TR 17603-31-05 Thermal design handbook - Part 5: Structural Materials: Metallic and Composite

TR 17603-31-06 Thermal design handbook - Part 6: Thermal Control Surfaces

TR 17603-31-07 Thermal design handbook - Part 7: Insulations

TR 17603-31-08 Thermal design handbook - Part 8: Heat Pipes

TR 17603-31-09 Thermal design handbook - Part 9: Radiators

TR 17603-31-10 Thermal design handbook - Part 10: Phase - Change Capacitors

TR 17603-31-11 Thermal design handbook - Part 11: Electrical Heating

TR 17603-31-12 Thermal design handbook - Part 12: Louvers

TR 17603-31-13 Thermal design handbook - Part 13: Fluid Loops

TR 17603-31-14 Thermal design handbook - Part 14: Cryogenic Cooling

TR 17603-31-15 Thermal design handbook - Part 15: Existing Satellites

TR 17603-31-16 Thermal design handbook - Part 16: Thermal Protection System