Novel Hybrid Ablative/Ceramic Layered Composite for Earth Re-entry Thermal Protection: Microstructural and Mechanical Performance

K. Triantou; K. Mergia; A. Marinou; G. Vekinis; J. Barcena; S. Florez; B. Perez; G. Pinaud; J. M. Bouilly; W. P.P. Fischer

doi:10.1007/s11665-015-1410-8

Novel Hybrid Ablative/Ceramic Layered Composite for Earth Re-entry Thermal Protection: Microstructural and Mechanical Performance

K. Triantou, K. Mergia, A. Marinou, G. Vekinis, J. Barcena, S. Florez, B. Perez, G. Pinaud, J. M. Bouilly, W. P.P. Fischer

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

11 Citations (Scopus)

Abstract

In view of spacecraft re-entry applications into planetary atmospheres, hybrid thermal protection systems based on layered composites of ablative materials and ceramic matrix composites are investigated. Joints of ASTERM™ lightweight ablative material with C_f/SiC (SICARBON™) were fabricated using commercial high temperature inorganic adhesives. Sound joints without defects are produced and very good bonding of the adhesive with both base materials is observed. Mechanical shear tests under ambient conditions and in liquid nitrogen show that mechanical failure always takes place inside the ablative material with no decohesion of the interface of the adhesive layer with the bonded materials. Surface treatment of the ablative surface prior to bonding enhances both the shear strength and the ultimate shear strain by up to about 60%.

Original language	English
Pages (from-to)	1452-1461
Number of pages	10
Journal	Journal of Materials Engineering and Performance
Volume	24
Issue number	4
DOIs	https://doi.org/10.1007/s11665-015-1410-8
Publication status	Published - Apr 2015

Keywords

adhesives
aerospace
ceramic
composites
mechanical
microscopy
optical metallography
static
x-ray
mycroscopy

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"

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10.1007/s11665-015-1410-8

Cite this

Triantou, K., Mergia, K., Marinou, A., Vekinis, G., Barcena, J., Florez, S., Perez, B., Pinaud, G., Bouilly, J. M., & Fischer, W. P. P. (2015). Novel Hybrid Ablative/Ceramic Layered Composite for Earth Re-entry Thermal Protection: Microstructural and Mechanical Performance. Journal of Materials Engineering and Performance, 24(4), 1452-1461. https://doi.org/10.1007/s11665-015-1410-8

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title = "Novel Hybrid Ablative/Ceramic Layered Composite for Earth Re-entry Thermal Protection: Microstructural and Mechanical Performance",

abstract = "In view of spacecraft re-entry applications into planetary atmospheres, hybrid thermal protection systems based on layered composites of ablative materials and ceramic matrix composites are investigated. Joints of ASTERM{\texttrademark} lightweight ablative material with Cf/SiC (SICARBON{\texttrademark}) were fabricated using commercial high temperature inorganic adhesives. Sound joints without defects are produced and very good bonding of the adhesive with both base materials is observed. Mechanical shear tests under ambient conditions and in liquid nitrogen show that mechanical failure always takes place inside the ablative material with no decohesion of the interface of the adhesive layer with the bonded materials. Surface treatment of the ablative surface prior to bonding enhances both the shear strength and the ultimate shear strain by up to about 60%.",

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doi = "10.1007/s11665-015-1410-8",

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Triantou, K, Mergia, K, Marinou, A, Vekinis, G, Barcena, J, Florez, S , Perez, B, Pinaud, G, Bouilly, JM & Fischer, WPP 2015, 'Novel Hybrid Ablative/Ceramic Layered Composite for Earth Re-entry Thermal Protection: Microstructural and Mechanical Performance', Journal of Materials Engineering and Performance, vol. 24, no. 4, pp. 1452-1461. https://doi.org/10.1007/s11665-015-1410-8

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AU - Mergia, K.

AU - Marinou, A.

AU - Vekinis, G.

AU - Barcena, J.

AU - Florez, S.

AU - Perez, B.

AU - Pinaud, G.

AU - Bouilly, J. M.

AU - Fischer, W. P.P.

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N2 - In view of spacecraft re-entry applications into planetary atmospheres, hybrid thermal protection systems based on layered composites of ablative materials and ceramic matrix composites are investigated. Joints of ASTERM™ lightweight ablative material with Cf/SiC (SICARBON™) were fabricated using commercial high temperature inorganic adhesives. Sound joints without defects are produced and very good bonding of the adhesive with both base materials is observed. Mechanical shear tests under ambient conditions and in liquid nitrogen show that mechanical failure always takes place inside the ablative material with no decohesion of the interface of the adhesive layer with the bonded materials. Surface treatment of the ablative surface prior to bonding enhances both the shear strength and the ultimate shear strain by up to about 60%.

AB - In view of spacecraft re-entry applications into planetary atmospheres, hybrid thermal protection systems based on layered composites of ablative materials and ceramic matrix composites are investigated. Joints of ASTERM™ lightweight ablative material with Cf/SiC (SICARBON™) were fabricated using commercial high temperature inorganic adhesives. Sound joints without defects are produced and very good bonding of the adhesive with both base materials is observed. Mechanical shear tests under ambient conditions and in liquid nitrogen show that mechanical failure always takes place inside the ablative material with no decohesion of the interface of the adhesive layer with the bonded materials. Surface treatment of the ablative surface prior to bonding enhances both the shear strength and the ultimate shear strain by up to about 60%.

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KW - static

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KW - adhesives

KW - aerospace

KW - ceramic

KW - composites

KW - mechanical

KW - mycroscopy

KW - optical metallography

KW - static

KW - x-ray

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Novel Hybrid Ablative/Ceramic Layered Composite for Earth Re-entry Thermal Protection: Microstructural and Mechanical Performance

Abstract

Keywords

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