Matrix materials such as cyanate esters have been developed which can survive short exposure to temperatures up to 370 degree C. A thermal protection system can extend the operating temperature limits of such organic based aerospace materials. A new class of polydimethylsiloxan matrix based composites was deveoped for use in thermal protection of missile launch structures. They are known as SM8000 and offer a threefold performance improvement compared with conventional phenolic-based composites. In this study we detail the process-property relationships for a cyanate ester/SM8000 hybrid system. In addition to a co-cure cycle, thermal and mechanical analyses have been performed. The interfacial fracture toughness tests performed on the cyanate ester (RS9E)/SM8000 specimems verified the robustness of the interface. The thermal decomposition behavior of the cyanate ester was improved by laminating with the SM80000 layer. An increase in modulus and strength have also been observed.
Cyanate ester composites Co-cured with a silicon-based thermal protection system
Co-Vernetzung von Cyanatester-Verbundwerkstoffen mit einem Hitzeschutzsystem auf Silikonbasis.
High Performance Polymers ; 14 , 3 ; 293-308
2002
16 Seiten, 16 Bilder, 2 Tabellen, 20 Quellen
Article (Journal)
English
Polymermatrix-Verbundwerkstoff , Laminat , Prepreg , glasfaserverstärkter Kunststoff , Polydimethylsiloxan , carbonfaserverstärkter Kunststoff , Cyanat , Polymer , Cyanursäure , Ester , Hybridverbundwerkstoff , Hitzeschild , Raketenbau , hitzebeständige Schutzschicht , Bruchzähigkeit , Vernetzung (Polymer)
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