Microstructural, thermal and ablative properties of TiB2 modified carbon fiber reinforced resorcinol formaldehyde composites for thermal protection of aerospace vehicle

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dc.contributor.authorAras, Sefa
dc.contributor.authorCavusoglu, Ferda Civan
dc.contributor.authorYilmaz, Nevin Gamze Karsli
dc.contributor.authorUnlu, Derya
dc.date.accessioned2026-02-08T15:14:48Z
dc.date.available2026-02-08T15:14:48Z
dc.date.issued2025
dc.departmentBursa Teknik Üniversitesi
dc.description.abstractAblative polymeric composites were fabricated using vacuum impregnation and hot press molding techniques. The composites consisted of needled carbon fiber felt as the reinforcing material and resorcinol-formaldehyde (RR) or boron-modified resorcinol-formaldehyde resin (RRB) as the matrix. Different weight percentages of titanium diboride (TiB2) were incorporated as a filler. The ablation mechanisms of the composites were derived from SEM-EDS, XPS, and XRD analysis of char layers formed after exposure to an oxyacetylene flame. The composites displayed excellent thermal insulation properties during the oxyacetylene test. The back surface temperatures ranged from 24.8 to 26.8 degrees C, indicating minimal heat penetration through the composites. This composite demonstrated a linear ablation rate (LAR) of 0.0053 mm/sec, a mass ablation rate (MAR) of 0.0195 g/sec, and a charring rate (CR) of 0.0543 mm/sec. During ablation, the low LAR, MAR, and CR values of C-RRB-T composites confirm that these composites are promising for thermal protection system applications in aerospace.Highlights Resorcinol formaldehyde matrix was modified with boron and filler TiB2. Composites were fabricated using vacuum impregnation and hot press molding. The thermal stability and char yields of the composites increased with TiB2. The addition of TiB2 to the C-RRB composite improved the ablation properties.
dc.description.sponsorshipTUBITAK [221M609]
dc.description.sponsorshipTUBITAK, Grant/Award Number: 221M609The financial support from the TUBITAK 221M609.
dc.identifier.doi10.1002/pc.29934
dc.identifier.endpage13348
dc.identifier.issn0272-8397
dc.identifier.issn1548-0569
dc.identifier.issue14
dc.identifier.scopus2-s2.0-105002292166
dc.identifier.scopusqualityQ1
dc.identifier.startpage13336
dc.identifier.urihttps://doi.org/10.1002/pc.29934
dc.identifier.urihttps://hdl.handle.net/20.500.12885/5445
dc.identifier.volume46
dc.identifier.wosWOS:001462813700001
dc.identifier.wosqualityQ2
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherWiley
dc.relation.ispartofPolymer Composites
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzWOS_KA_20260207
dc.subjectablation
dc.subjectcarbon fiber-reinforced resorcinol formaldehyde resin composites
dc.subjectphenylboronic acid
dc.subjectthermal protection systems
dc.subjecttitanium diboride
dc.titleMicrostructural, thermal and ablative properties of TiB2 modified carbon fiber reinforced resorcinol formaldehyde composites for thermal protection of aerospace vehicle
dc.typeArticle

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