document title / titre du document TRP W ORK PLAN ... - emits - ESA

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TRP Work Plan 2005-2007 Description of Activities TEC-SB/7935/dc 12/Feb/09 TRP Reference: Title: T406-12MP Preparation of an electrodynamic-heatshield flight experiment It is the objective of the present work to prepare a flight demonstration experiment by looking into the available magnet technology with regard to technical performance and cost consideration and by performing preliminary on-ground tests. The boundary conditions imposed by a reentry capsule and its launch vehicle shall be taken into account. The focus of this work will deal with the coil section (nose of the capsule), which must contain the superconducting coil and its magnetic screen. Deliverables: Experimental demonstration/modeling. Current TRL: - Target TRL: TRL1-2 Application Need/Date: TRL5 by 2015 Application/Mission: re-entry vehicles Contract Duration: 18 months SW Clause : - Dossier0 Ref.: T-7715 Consistency with Harmonisation Roadmap and Conclusions: TRP Reference: T406-13MP Title: Advanced Methods for Hypersonic plasma - flow control The objective of the present proposal is to advance new techniques to control the flow within the hypersonic shock layer of space transportation systems entering planets or re-entering earth at hypersonic speeds. A promising very innovative concept is the one of controlling the flow pattern through electro-magnetic forces acting on the ionized component of the flow impacting the vehicle. This electro – magnetic interaction of the flow could potentially: • Reduce locally the heat flux via shock standoff increase. • Increase wave drag thereby also reduce heat load due to reduction of ballistic coefficient. • Be used to control the flow for stability and trimming resulting in simplification or elimination of RCS. • Manipulate black out periods and therefore optimize communication links. The purpose is to build up further on recent advances made in the HEAT and L2K facilities and to take advantage of the ongoing associated activities within the CIRA CAST and DLR programmes. The following activities are proposed : • Small scale experiments in HEAT and L2K thereby augmenting their expertise in this field including numerical rebuilding. • Developments of associated intrusive and non intrusive diagnostic measurement for later use in SCIROCCO. • Preparatory activities for SCIROCCO testing compatible with CAST. • Study on potential system impact for possible future application and in flight demonstration. Deliverables: Technical note Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2011 Exploration and Science Planetary Entry Application/Mission: Contract Duration: 24 months and Earth Reentry missions SW Clause : - Dossier0 Ref.: T-7715 Consistency with Harmonisation Roadmap: “Aerothermodynamics Tools”, 2007; Conclusions: 1st semester 2007 Roadmap and Conclusions: Page 97 of 227
TRP Work Plan 2005-2007 Description of Activities TEC-SB/7935/dc 12/Feb/09 4.8.1 - Aerothermodynamics (Source: TRP 2000-2003) TRP Reference: Title: 03/MPA-001 In-Flight Aerothermodynamic Measurements Deliverables: Current TRL: Target TRL: Application Need/Date: Application/Mission: Contract Duration: SW Clause : - Dossier0 Ref.: Consistency with Harmonisation Roadmap and Conclusions: TRP Reference: 94/8.2.1.4, 03/MPA-002 Title: Plasma Radiation Database Radiative heat fluxes represent a significant contribution to wall heat flux and are not sufficiently precisely evaluated with tools and databases presently available in Europe. The prediction of plasma emission and absorption is important for Earth atmospheric entries at high velocities (typical of Sample Return missions), for high velocity entries into Mars and Venus atmospheres (typically above 9km/s) and for entries in atmospheres where dissociation produces strong radiators (e.g. Titan). Radiation plays also a major role in the thermal environment of solid rocket engines. A good knowledge of the radiative contribution to heat flux is already necessary in phase A and assessment studies, because of its large influence on the mass budget of the vehicle. ESA has initiated, under the Technology Research Programme (TRP) an initial development of a code and an experimental database for the determination of radiative heat flux: PARADE. This code is limited so far to some atoms and diatomic molecules, but should be extended to triatomic molecules such as CO2, major component of Mars atmosphere. PARADE new additions should be validated in order to become fully useful for the design of thermal protection systems. The objective of the study is to further develop and validate (by appropriate validation test when applicable) a code and to create an experimental database for thermal radiation of plasma (emission and absorption). Such a code should extend the present PARADE possibilities to include triatomic molecular species. Deliverables: Database model / notes. Current TRL: Algorith Target TRL: m Prototype Application Need/Date: TRL5 by 2009-2010 ExoMars, Mars Sample return, or for Application/Mission: missions to Venus (EVE), NEO missions Contract Duration: 12 months (Marco Polo) SW Clause : - Dossier0 Ref.: T-7902 Consistency with Harmonisation Roadmap and Conclusions: Page 98 of 227
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