Heat shield technology for a reusable ballistic stage
Abstract
Thermal protection technology status was reviewed, and the heat shielding of a two-stage launcher with reusable first stage having engines-first reentry was studied. Design criteria are established to evaluate the most suitable heat shield system and the heat shield mass for various heat loads. The high heat flow rates from thruster exhaust are determined by protection system size. Only ablative or water cooled structures are feasible. It is found that ablation has weight advantages, but is more expensive.
- Publication:
-
In CNES The Future of Launchers in Europe
- Pub Date:
- 1982
- Bibcode:
- 1982cnes.rept..497B
- Keywords:
-
- Ballistic Trajectories;
- Heat Shielding;
- Reentry Shielding;
- Reusable Launch Vehicles;
- Ablation;
- Liquid Cooling;
- Technology Assessment;
- Thermal Protection;
- Launch Vehicles and Space Vehicles