Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications

K.I. Triantou; K. Mergia; B. Perez; S. Florez; A. Stefan; C. Ban; G. Pelin; G. Ionescu; C. Zuber; W.P.P. Fischer; J. Barcena

doi:10.1016/j.compositesb.2016.12.020

Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications

K.I. Triantou, K. Mergia, B. Perez, S. Florez, A. Stefan, C. Ban, G. Pelin, G. Ionescu, C. Zuber, W.P.P. Fischer, J. Barcena

Research output: Contribution to journal › Article › peer-review

72 Citations (Scopus)

Abstract

Hybrid thermal protection systems for aerospace applications based on carbon-bonded carbon fiber composite (CALCARB®) and ceramic matrix composites have been investigated. Two types of ceramic composite materials were considered, Cf/SiC (SiCARBON™) and C/C-SiC. The ablative material and the ceramic matrix composite were joined using alumina, graphite and zirconia-zirconium silicate based commercial high temperature adhesives and their performance on thermal shock tests was evaluated. Microstructural analysis of the joints after thermal shock tests was conducted using optical microscopy and scanning electron microscopy (SEM) coupled with energy dispersive spectroscopy (EDS). Both material combinations survive the thermal shock tests for the structures in which zirconia-zirconium silicate and graphite based adhesives were employed.

Original language	English
Pages (from-to)	270-278
Number of pages	9
Journal	Composites Part B: Engineering
Volume	111
DOIs	https://doi.org/10.1016/j.compositesb.2016.12.020
Publication status	Published - 15 Feb 2017

Keywords

Ceramic-matrix composites (CMCs)
High-temperature properties
Electron microscopy
Joints/joining

Project and Funding Information

Project ID
info:eu-repo/grantAgreement/EC/FP7/283797/EU/HYBRID ABLATIVE DEVELOPMENT FOR RE-ENTRY IN PLANETARY ATMOSPHERIC THERMAL PROTECTION/HYDRA
Funding Info
European Project ‘‘HYDRA’’ (G.A. n. 283797) with the financial support by the European Commission.

Access to Document

10.1016/j.compositesb.2016.12.020

Cite this

Triantou, K. I., Mergia, K., Perez, B., Florez, S., Stefan, A., Ban, C., Pelin, G., Ionescu, G., Zuber, C., Fischer, W. P. P., & Barcena, J. (2017). Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications. Composites Part B: Engineering, 111, 270-278. https://doi.org/10.1016/j.compositesb.2016.12.020

@article{085c637a73184c13b9b4d4d7399e06b6,

title = "Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications",

abstract = "Hybrid thermal protection systems for aerospace applications based on carbon-bonded carbon fiber composite (CALCARB{\textregistered}) and ceramic matrix composites have been investigated. Two types of ceramic composite materials were considered, Cf/SiC (SiCARBON{\texttrademark}) and C/C-SiC. The ablative material and the ceramic matrix composite were joined using alumina, graphite and zirconia-zirconium silicate based commercial high temperature adhesives and their performance on thermal shock tests was evaluated. Microstructural analysis of the joints after thermal shock tests was conducted using optical microscopy and scanning electron microscopy (SEM) coupled with energy dispersive spectroscopy (EDS). Both material combinations survive the thermal shock tests for the structures in which zirconia-zirconium silicate and graphite based adhesives were employed.",

keywords = "Ceramic-matrix composites (CMCs), High-temperature properties, Electron microscopy, Joints/joining, Ceramic-matrix composites (CMCs), High-temperature properties, Electron microscopy, Joints/joining",

author = "K.I. Triantou and K. Mergia and B. Perez and S. Florez and A. Stefan and C. Ban and G. Pelin and G. Ionescu and C. Zuber and W.P.P. Fischer and J. Barcena",

note = "Publisher Copyright: {\textcopyright} 2016 Elsevier Ltd",

year = "2017",

month = feb,

day = "15",

doi = "10.1016/j.compositesb.2016.12.020",

language = "English",

volume = "111",

pages = "270--278",

journal = "Composites Part B: Engineering",

issn = "1879-1069",

}

Triantou, KI, Mergia, K, Perez, B , Florez, S, Stefan, A, Ban, C, Pelin, G, Ionescu, G, Zuber, C, Fischer, WPP & Barcena, J 2017, 'Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications', Composites Part B: Engineering, vol. 111, pp. 270-278. https://doi.org/10.1016/j.compositesb.2016.12.020

TY - JOUR

T1 - Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications

AU - Triantou, K.I.

AU - Mergia, K.

AU - Perez, B.

AU - Florez, S.

AU - Stefan, A.

AU - Ban, C.

AU - Pelin, G.

AU - Ionescu, G.

AU - Zuber, C.

AU - Fischer, W.P.P.

AU - Barcena, J.

PY - 2017/2/15

Y1 - 2017/2/15

N2 - Hybrid thermal protection systems for aerospace applications based on carbon-bonded carbon fiber composite (CALCARB®) and ceramic matrix composites have been investigated. Two types of ceramic composite materials were considered, Cf/SiC (SiCARBON™) and C/C-SiC. The ablative material and the ceramic matrix composite were joined using alumina, graphite and zirconia-zirconium silicate based commercial high temperature adhesives and their performance on thermal shock tests was evaluated. Microstructural analysis of the joints after thermal shock tests was conducted using optical microscopy and scanning electron microscopy (SEM) coupled with energy dispersive spectroscopy (EDS). Both material combinations survive the thermal shock tests for the structures in which zirconia-zirconium silicate and graphite based adhesives were employed.

AB - Hybrid thermal protection systems for aerospace applications based on carbon-bonded carbon fiber composite (CALCARB®) and ceramic matrix composites have been investigated. Two types of ceramic composite materials were considered, Cf/SiC (SiCARBON™) and C/C-SiC. The ablative material and the ceramic matrix composite were joined using alumina, graphite and zirconia-zirconium silicate based commercial high temperature adhesives and their performance on thermal shock tests was evaluated. Microstructural analysis of the joints after thermal shock tests was conducted using optical microscopy and scanning electron microscopy (SEM) coupled with energy dispersive spectroscopy (EDS). Both material combinations survive the thermal shock tests for the structures in which zirconia-zirconium silicate and graphite based adhesives were employed.

KW - Ceramic-matrix composites (CMCs)

KW - High-temperature properties

KW - Electron microscopy

KW - Joints/joining

KW - Ceramic-matrix composites (CMCs)

KW - High-temperature properties

KW - Electron microscopy

KW - Joints/joining

UR - http://www.scopus.com/inward/record.url?scp=85006789643&partnerID=8YFLogxK

U2 - 10.1016/j.compositesb.2016.12.020

DO - 10.1016/j.compositesb.2016.12.020

M3 - Article

SN - 1879-1069

VL - 111

SP - 270

EP - 278

JO - Composites Part B: Engineering

JF - Composites Part B: Engineering

ER -

Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications

Abstract

Keywords

Project and Funding Information

Access to Document

Other files and links

Fingerprint

Cite this