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Advanced European Re-Entry System Based on Inflatable Heat Shields EFESTO project overview: system and mission design and technology roadmap

Trovarelli, F. and Guidotti, Guiseppe and Medici, G. and Schleutker, Thorn and Dietlein, Ingrid Monika and Gambaccani, G. and Governale, Guiseppe and Verant, Jean-Luc and Dauvois, Y. and Prevereaud, Ysolde (2021) Advanced European Re-Entry System Based on Inflatable Heat Shields EFESTO project overview: system and mission design and technology roadmap. In: Proceedings of the International Astronautical Congress, IAC. International Astronautical Congress (IAC 2021), 25.-29.10.2021, Dubai, United Arab Emirates. ISSN 0074-1795.

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Official URL: https://iafastro.directory/iac/archive/browse/IAC-21/D2/3/66011/


The European Union H2020 EFESTO project is coordinated by DEIMOS Space with the end goals of improving the European TRL of Inflatable Heat Shields for re-entry vehicles (from 3 to 4/5) and paving the way towards further improvements (TRL 6 with a future In-Orbit Demonstrator, IOD). This paper provides an overview of the project, the consolidated results of the detailed design of atmospheric entry missions for Mars exploration and Earth applications and an overview of the technology roadmap. The project includes design and ground tests activities, covering the key subsystems of inflatable structure and flexible TPS that compose a Hypersonic Inflatable Aerodynamic Decelerator (HIAD). Two key applications, have been identified to enable Mars Robotic Exploration and Reusable Small Launchers Upper Stages. For the Mars Application, the robotic exploration mission design results in a 9m diameter Hypersonic Inflatable Aerodynamic Decelerator (HIAD) class, combined with Supersonic Retro-Propulsion for safely landing the 2.5 ton payload at MOLA +3km target altitude. For the Earth Application, the VEGA upper stage (AVUM) has been selected as baseline case study. The current mission foresees a deorbiting from Polar Orbit followed by a controlled entry phase (Ballistic Coefficient of about 46 kg/m2). Deceleration is achieved using a 4.5m diameter class HIAD combined with parachutes during the descent phase, A parafoil enables Mid-Air-Capturing (MAR) of the entry vehicle with a helicopter. For the Mars applications, the mission analysis shows that, compared to state-of-the-art technology, implementation of the HIAD efficiently provides larger drag during the entry phase, thus allowing to increase both landed mass and MOLA altitude at which a soft landing is possible. For the Earth applications, the mission analysis confirms the HIAD as an appealing, performing and robust solution for the purpose of safely returning the VEGA upper stage to a targeted recovery area. These results demonstrate that HIAD systems represent an enabling technology for the next class of high-mass Mars exploration missions and this technology can be key in reducing the cost of access to space through upper stage reusability. The need for advancing the TRL of this technology, which is the primary objective of the EFESTO project, is thus confirmed and the relevance of an IOD mission that will enhance the European know-how in the field, of which the EFESTO consortium represents the core, is reinforced. This project has received funding from the European Union’s Horizon 2020 research and innovation programme under grant agreement No 821801.

Item URL in elib:https://elib.dlr.de/147676/
Document Type:Conference or Workshop Item (Speech)
Title:Advanced European Re-Entry System Based on Inflatable Heat Shields EFESTO project overview: system and mission design and technology roadmap
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Schleutker, ThornUNSPECIFIEDhttps://orcid.org/0000-0002-1833-2850UNSPECIFIED
Governale, GuiseppePolitecnico di TorinoUNSPECIFIEDUNSPECIFIED
Journal or Publication Title:Proceedings of the International Astronautical Congress, IAC
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:EFESTO, FTPS, Infaltor, Entry Flight, Flexibel TPS, Inflatable Heat Shield
Event Title:International Astronautical Congress (IAC 2021)
Event Location:Dubai, United Arab Emirates
Event Type:international Conference
Event Dates:25.-29.10.2021
Organizer:International Astronautical Federation (IAF)
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:other
DLR - Research area:Raumfahrt
DLR - Program:R - no assignment
DLR - Research theme (Project):R - no assignment
Location: Bremen , Köln-Porz
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Institute of Space Systems > Space Launcher Systems Analysis
Deposited By: Schleutker, Thorn
Deposited On:10 Jan 2022 09:37
Last Modified:10 Jan 2022 09:37

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