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C3HARME SIGNED

NEXT GENERATION CERAMIC COMPOSITES FOR COMBUSTION HARSH ENVIRONMENTS AND SPACE

Total Cost €

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EC-Contrib. €

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Partnership

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 C3HARME project word cloud

Explore the words cloud of the C3HARME project. It provides you a very rough idea of what is the project "C3HARME" about.

2500    hybrid    ceramic    technologies    hypersonic    near    materials    intrinsic    vibrations    propellants    centered    consolidated    temperatures    fluxes    severe    aggressive    starts    deg    extended    combustion    earth    projected    heating    operation    mwm    hot    3500    thermochemical    chambers    2700    extremely    sic    purpose    nozzles    damage    intense    ablation    aerospace    fabricated    matrix    assembled    15    ambient    dimensional    validated    flying    environment    firing    class    innovative    easily    harsh    dimensions    tps    enriched    repairing    balanced    validate    re    ultra    cooling    medical    chemically    energy    mechanical    mix    convective    stability    tiles    thermal    withstand    heat    corrosive    rocket    thanks    temperature    realistic    nuclear    space    situ    innovation    companies    mach    industrial    launch    performance    risk    preforms    c3harme    survive    composites    service    manufacture    zero    notch    uhtcs    demand    atmosphere    rapid    shape    entry    flight    smes    fibres    uhtcmcs    environments    trl    there    suitable    capability    partnership    motors    scalable    erosion    ceramics    protection    performing    vehicles    combination    mitigating    solid   

Project "C3HARME" data sheet

The following table provides information about the project.

Coordinator
CONSIGLIO NAZIONALE DELLE RICERCHE 

Organization address
address: PIAZZALE ALDO MORO 7
city: ROMA
postcode: 185
website: www.cnr.it

contact info
title: n.a.
name: n.a.
surname: n.a.
function: n.a.
email: n.a.
telephone: n.a.
fax: n.a.

 Coordinator Country Italy [IT]
 Project website http://c3harme.eu/
 Total cost 8˙033˙034 €
 EC max contribution 8˙033˙034 € (100%)
 Programme 1. H2020-EU.2.1.3. (INDUSTRIAL LEADERSHIP - Leadership in enabling and industrial technologies - Advanced materials)
 Code Call H2020-NMP-2015-two-stage
 Funding Scheme RIA
 Starting year 2016
 Duration (year-month-day) from 2016-06-01   to  2020-05-31

 Partnership

Take a look of project's partnership.

# participants  country  role  EC contrib. [€] 
1    CONSIGLIO NAZIONALE DELLE RICERCHE IT (ROMA) coordinator 1˙266˙362.00
2    DEUTSCHES ZENTRUM FUER LUFT - UND RAUMFAHRT EV DE (KOELN) participant 1˙336˙534.00
3    AVIO SPA IT (ROMA) participant 988˙133.00
4    FUNDACION TECNALIA RESEARCH & INNOVATION ES (DERIO BIZKAIA) participant 986˙319.00
5    THE UNIVERSITY OF BIRMINGHAM UK (BIRMINGHAM) participant 678˙861.00
6    UNIVERSITA DEGLI STUDI DI NAPOLI FEDERICO II IT (NAPOLI) participant 500˙962.00
7    AIRBUS DEFENCE AND SPACE GMBH DE (TAUFKIRCHEN) participant 465˙089.00
8    ARIANEGROUP GMBH DE (TAUFKIRCHEN) participant 448˙879.00
9    NANOKER RESEARCH SL ES (OVIEDO) participant 391˙729.00
10    IN SRL IT (UDINE) participant 390˙159.00
11    FHP- FREZITE HIGH PERFORMANCE LDA PT (PORTO) participant 340˙500.00
12    THE PROVOST, FELLOWS, FOUNDATION SCHOLARS & THE OTHER MEMBERS OF BOARD OF THE COLLEGE OF THE HOLY & UNDIVIDED TRINITY OF QUEEN ELIZABETH NEAR DUBLIN IE (DUBLIN) participant 239˙502.00
13    AIRBUS DS GMBH DE (TAUFKIRCHEN) participant 0.00
14    AVIO SPA IT (ROMA) participant 0.00

Map

 Project objective

There is an increasing demand for advanced materials with temperature capability in highly corrosive environments for aerospace. Rocket nozzles of solid/hybrid rocket motors must survive harsh thermochemical and mechanical environments produced by high performance solid propellants (2700-3500°C). Thermal protection systems (TPS) for space vehicles flying at Mach 7 must withstand projected service temperatures up to 2500°C associated to convective heat fluxes up to 15 MWm-2 and intense mechanical vibrations at launch and re-entry into Earth’s atmosphere. The combination of extremely hot temperatures, chemically aggressive environments and rapid heating/cooling is beyond the capabilities of current materials. Main purpose of C3HARME is to design, develop, manufacture, test and validate a new class of out-performing, reliable, cost-effective and scalable Ultra High Temperature Ceramic Matrix Composites (UHTCMCs) based on C or SiC fibres/preforms enriched with ultra-high temperature ceramics (UHTCs) capable of in-situ repairing damage induced during operation in severe aerospace environments. C3HARME will apply to two main applications: near-ZERO erosion rocket nozzles that must maintain dimensional stability during firing in combustion chambers, and near-ZERO ablation thermal protection systems enabling hypersonic space vehicles to maintain flight performance. C3HARME represents a well-balanced mix of innovative and consolidated technologies, mitigating the level of risk intrinsic in top-notch research and innovation development. C3HARME starts from TRL of 3-4 and focuses on TRL 6 thanks to a strong industrial partnership, including SMEs and large companies. To reach TRL 6, rocket nozzles and TPS tiles with realistic dimensions and shape will be fabricated, assembled into a suitable system, and validated in a relevant ambient (environment centered test). Project results could be easily extended to the energy, medical and/or nuclear environments.

 Deliverables

List of deliverables.
Catalogue of innovations risks - month 24 Documents, reports 2019-08-30 14:07:31
Specific set of recommendations for material development in WP2 based on micro-models / DFT Documents, reports 2019-08-30 14:07:31
Summary D2.1, 2.2, 2.3, 2.4 Documents, reports 2019-08-30 14:07:31
Atomistic modelling of processes at materials interfaces Documents, reports 2019-08-30 14:07:31
Visual identity kit - 12 month Documents, reports 2019-08-30 14:07:29
Catalogue of innovations risks - month 12 Documents, reports 2019-08-30 14:07:29

Take a look to the deliverables list in detail:  detailed list of C3HARME deliverables.

 Publications

year authors and title journal last update
List of publications.
2018 Yanhui Zhang, Stefano Sanvito
First‐principles investigation of the thermodynamic stability of M B 2 materials surfaces ( M  = Ti/Zr/Hf)
published pages: 4118-4127, ISSN: 0002-7820, DOI: 10.1111/jace.15547
Journal of the American Ceramic Society 101/9 2019-08-30
2017 Antonio Vinci, Luca Zoli, Elena Landi, Diletta Sciti
Oxidation behaviour of a continuous carbon fibre reinforced ZrB 2 –SiC composite
published pages: 129-138, ISSN: 0010-938X, DOI: 10.1016/j.corsci.2017.04.012
Corrosion Science 123 2019-08-30
2019 Antonio Vinci, Luca Zoli, Diletta Sciti, Jeremy Watts, Greg E. Hilmas, William G. Fahrenholtz
Mechanical behaviour of carbon fibre reinforced TaC/SiC and ZrC/SiC composites up to 2100°C
published pages: 780-787, ISSN: 0955-2219, DOI: 10.1016/j.jeurceramsoc.2018.11.017
Journal of the European Ceramic Society 39/4 2019-08-30
2018 R. Savino, S. Mungiguerra, G. D. Di Martino
Testing ultra-high-temperature ceramics for thermal protection and rocket applications
published pages: s9-s18, ISSN: 1743-6753, DOI: 10.1080/17436753.2018.1509175
Advances in Applied Ceramics 117/sup1 2019-08-30
2018 V. Rubio, P. Ramanujam, J. Binner
Ultra-high temperature ceramic composite
published pages: s56-s61, ISSN: 1743-6753, DOI: 10.1080/17436753.2018.1475140
Advances in Applied Ceramics 117/sup1 2019-08-30
2018 Mungiguerra Stefano
Arc-Jet testing of ultra-high-temperature ceramic matrix composites for aerospace applications.
published pages: , ISSN: , DOI: 10.5281/zenodo.2551293
First Workshop for Young Ceramists, Bologna, Italy, 26-27 November 2018 2019-08-30
2018 Marius Kütemeyer, Thomas Helmreich, Stefan Rosiwal, Dietmar Koch
Influence of zirconium-based alloys on manufacturing and mechanical properties of ultra high temperature ceramic matrix composites
published pages: s62-s69, ISSN: 1743-6753, DOI: 10.1080/17436753.2018.1509810
Advances in Applied Ceramics 117/sup1 2019-08-30
2018 Luca Zoli, Pietro Galizia, Laura Silvestroni, Diletta Sciti
Synthesis of group IV and V metal diboride nanocrystals via borothermal reduction with sodium borohydride
published pages: 2627-2637, ISSN: 0002-7820, DOI: 10.1111/jace.15401
Journal of the American Ceramic Society 101/6 2019-08-30
2018 Pietro Galizia, Simone Failla, Luca Zoli, Diletta Sciti
Tough salami-inspired Cf/ZrB2 UHTCMCs produced by electrophoretic deposition
published pages: 403-409, ISSN: 0955-2219, DOI: 10.1016/j.jeurceramsoc.2017.09.047
Journal of the European Ceramic Society 38/2 2019-08-30
2018 Vinci Antonio
Processing and characterization of carbon fibre reinforced ZrB2/SiC/WC composites
published pages: , ISSN: , DOI: 10.5281/zenodo.2551275
First Workshop for Young Ceramists, Bologna, Italy, 26-27 November 2018 2019-08-30
2018 Antonio Vinci, Luca Zoli, Diletta Sciti, Cesare Melandri, Stefano Guicciardi
Understanding the mechanical properties of novel UHTCMCs through random forest and regression tree analysis
published pages: 97-107, ISSN: 0264-1275, DOI: 10.1016/j.matdes.2018.02.061
Materials & Design 145 2019-08-30
2018 Antonio Vinci, Luca Zoli, Diletta Sciti
Influence of SiC content on the oxidation of carbon fibre reinforced ZrB 2 /SiC composites at 1500 and 1650 °C in air
published pages: 3767-3776, ISSN: 0955-2219, DOI: 10.1016/j.jeurceramsoc.2018.04.064
Journal of the European Ceramic Society 38/11 2019-08-30
2019 S. Failla, P. Galizia, L. Zoli, A. Vinci, D. Sciti
Toughening effect of non-periodic fiber distribution on crack propagation energy of UHTC composites
published pages: 612-618, ISSN: 0925-8388, DOI: 10.1016/j.jallcom.2018.11.043
Journal of Alloys and Compounds 777 2019-08-30
2018 Di Martino Giuseppe D.; Mungiguerra Stefano; Cecere Anselmo; Savino Raffaele; Vinci Antonio; Zoli Luca; Sciti Diletta
Hybrid rockets with nozzle in ultra-high-temperature ceramic composites
published pages: , ISSN: , DOI: 10.5281/zenodo.1473368
69th International Astronautical Congress (IAC) 1 2019-08-30
2018 Luca Zoli, Antonio Vinci, Pietro Galizia, Cesare Melandri, Diletta Sciti
On the thermal shock resistance and mechanical properties of novel unidirectional UHTCMCs for extreme environments
published pages: , ISSN: 2045-2322, DOI: 10.1038/s41598-018-27328-x
Scientific Reports 8/1 2019-08-30
2018 Raffaele Savino, Luigi Criscuolo, Giuseppe Daniele Di Martino, Stefano Mungiguerra
Aero-thermo-chemical characterization of ultra-high-temperature ceramics for aerospace applications
published pages: 2937-2953, ISSN: 0955-2219, DOI: 10.1016/j.jeurceramsoc.2017.12.043
Journal of the European Ceramic Society 38/8 2019-08-30
2018 Laura Silvestroni, Kerstin Stricker, Diletta Sciti, Hans-Joachim Kleebe
Understanding the oxidation behavior of a ZrB 2 –MoSi 2 composite at ultra-high temperatures
published pages: 216-228, ISSN: 1359-6454, DOI: 10.1016/j.actamat.2018.03.042
Acta Materialia 151 2019-08-30
2017 L. Zoli, A. Vinci, L. Silvestroni, D. Sciti, M. Reece, S. Grasso
Rapid spark plasma sintering to produce dense UHTCs reinforced with undamaged carbon fibres
published pages: 1-7, ISSN: 0264-1275, DOI: 10.1016/j.matdes.2017.05.029
Materials & Design 130 2019-08-30
2018 Mungiguerra Stefano; Di Martino Giuseppe D.; Cecere Anselmo; Savino Raffaele; Zoli Luca; Silvestroni Laura; Sciti Diletta
Characterization of carbon-fiber reinforced ultra-high-temperature ceramic matrix composites in arc-jet environment
published pages: , ISSN: , DOI: 10.5281/zenodo.1473396
69th International Astronautical Congress (IAC) 1 2019-08-30
2017 L. Zoli, D. Sciti
Efficacy of a ZrB2–SiC matrix in protecting C fibres from oxidation in novel UHTCMC materials
published pages: 207-213, ISSN: 0264-1275, DOI: 10.1016/j.matdes.2016.09.104
Materials & Design 113 2019-08-30

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