The thermo-mechanical architecture and TPS configuration of the pre-X vehicle
The thermo-mechanical architecture and TPS configuration of the pre-X vehicle
- New search for: Leleu, F.
- New search for: Watillon, Ph.
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- New search for: Lacombe, A.
- New search for: Soyris, Ph.
- New search for: Leleu, F.
- New search for: Watillon, Ph.
- New search for: Moulin, J.
- New search for: Lacombe, A.
- New search for: Soyris, Ph.
AbstractThis paper reviews both the thermo-mechanical architecture and the configuration of the thermal protection system (TPS) of the Pre-X vehicle, as presented at the System Concept Review that concluded the evaluation phase in June 2002. Pre-X is a first generation experimental re-entry vehicle. It aims mainly at gathering aerothermodynamics (ATD) data in the hypersonic regime and at testing reusable thermal protections and hot structures, currently available in Europe, which could be used for a RLV. The mechanical architecture, based on an aircraft like metallic structure, is presented, as well as the general configuration of the TPS. The experimentation plan on thermal protections is detailed; it includes ceramic matrix composite (CMC) hot structures, ceramic shingles and panels, metallic components, flexible blankets. The outcomes of the analyses already performed on critical issues are summarized (oxidation regime of C/SiC, radiation box analysis on the nose cap, windward and body-flaps pre-design and pre-sizing). Finally, guidelines are proposed for the development plan of the TPS and an outline is given on tasks which are under investigation.
Document information
The thermo-mechanical architecture and TPS configuration of the pre-X vehicle
Acta Astronautica ; 56 , 4 ; 453-464
2004-05-04
12 pages
Article (Journal)
Electronic Resource
English
ARD , atmospheric re-entry demonstrator , ATD , aerothermodynamics , CMC , ceramic matrix composite , C/SiC , carbon/silicon carbide , EADS-LV , EADS LAUNCH VEHICLES , FEI , flexible external insulation , ODS , oxide dispersion strengthened , RCS , reaction control system , RLV , reusable launch vehicle , SPFI , surface protected flexible insulation , SPS , SNECMA solid propulsion , TRL , technology readiness level , TPS , thermal protection system , wrt , with respect to.
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