| Popis: |
Future reusable space transportation vehicles require lightweight structures which are resistant to high temperatures and which can be reused for a certain number of flights with a minimum effort of servicing. Dasa has developed a CMC manufacturing process that allows the fabrication of complex and large integral hot structures in carbon-silicon carbide such as nose caps, panels and leading edges. The Polymer Pyrolysis Process applied is more cost efficient and requires only a minimum fabrication period compared to other CMC fabrication methods. This paper reports about present work at Dasa with respect to design, manufacturing and test of large integral hot CMC structures for future launchers, capsules and space probes. Abbreviations C/SiC carbon fiber reinforced silicon carbide CFRP carbon fiber reinforced polymers CMC ceramic matrix composites CVD chemical vapor deposition CVI chemical vapor infiltration DARA German Space Agency Dasa Daimler-Benz Aerospace AG ESA European Space Agency MDA Me Donnell Douglas Aerospace NDI non-destructive inspection OPS oxidation protective system PPP Infiltration and Pyrolysis of Silicon Polymeres Process, or shortly "Polymere Pyrolysis Process" SSTO Single Stage to Orbit TPS thermal protection system ..Copyright © by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved." |
