Abstract
Epoxy/carbon fiber composites are widely used as structural materials in the aerospace field. Improving the ablation resistance of epoxy/carbon fiber composites is of great importance for the fabrication of highly integrated structural-thermal protection materials. In this study, a silicon-modified epoxy/carbon fiber composite was prepared by a hyperbranched structural design approach. By taking advantage of the excellent antioxidant properties of the silicone compounds generated by the pyrolysis of hyperbranched silicone structures, a dense char layer is rapidly constructed on the surface of composites. The characterization and thermal pyrolysis behavior of hyperbranched silicone-modified epoxy resins are analyzed. In the simulated aerodynamic environment of a high-speed vehicle (where the heat flow is 160 kW/m2), compared with epoxy/CF composites, the value of the mass loss rate of modified composites underwent a reduction exceeding 80%, accompanied by a 60.3 °C decrease in the maximum back-surface temperature. More significantly, the post-ablation mechanical properties were evaluated through a three-point bending test, revealing that the modified composites retained over 95% of their initial flexural strength and modulus after simulated pneumatic heating. This approach offers a new approach to manufacture structurally simple, integrated structure-thermal protection systems.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
