Safety Analysis for the Nose cap of a launch re-entry vehicle
- Paper number
IAC-09.C2.I.8
- Author
Mr. Michele Ferraiuolo, CIRA S.C.P.A., Italy
- Coauthor
Dr. Aniello Riccio, CIRA Italian Aerospace Research Centre, Italy
- Coauthor
Dr. Domenico Tescione, CIRA Italian Aerospace Research Centre, Italy
- Coauthor
Dr. Giuliano Marino, CIRA Italian Aerospace Research Centre, Italy
- Year
2009
- Abstract
The present work has been developed within CIRA USV (Unmanned Space Vehicle)-SHS (Sharp Hot Structures) activities focused on the applicability of Ultra High Temperature Ceramics (UHTC) for “hot structure” applications, leading to the replacement of conventional TPS concepts in zones subjected to very high thermal loads such as Nose cap and wing leading edge. UHTC materials are particularly suitable for those components since they are able to sustain temperatures up to around 2800 K and tolerate the thermal solicitations occurring during the re-entry phase of space vehicles exposed to high aero-thermal fluxes. The present work describes the safety analysis performed on the test article representing the Nose cap of a launch re-entry vehicle that is going to be tested in the Plasma Wind Tunnel. Transient Thermal and Static Structural non-linear Finite element analyses have been performed in order to verify that no failure phenomena will occur on the Test Article and no damages for the PWT test facility will be encountered. The aim of the test is to investigate the behaviour of ceramic Sharp Hot Structures under the aero-thermal loads encountered by the USV vehicle when re-entering Earth’s atmosphere.
- Abstract document
- Manuscript document
(absent)