Characterization of prepreg and cured epoxy/fiberglass composite material for use in advanced composite piping systems

摘要: Abstract A company that uses epoxy/fiberglass prepreg material in advanced composite piping systems requested the NASA/Marshall Space Flight Center (MSFC) use several thermal analysis techniques to characterize material. Dynamic and isothermal tests by of TA Instruments 2920 Differential Scanning Calorimeter (DSC) yielded cure kinetics on prepreg. The dynamic data showed two exothermic reactions for prepreg, but first exotherm was a low temperature event began disappear near 105°C. For second exotherm, activation energies ( E 2 ) 79.0 87.1 kJ/mol were obtained from data, respectively. Partial temperatures times glass transition T g versus conversion plot with an approximate gelation point at 63% conversion. At 135°C 103°C, most ultimate achieved. 983 Mechanical Analyzer (DMA) 140 1 50.5 kJ/mol reactions, respectively, based seyeral temperatures. DMA sweep fixed frequencies average energy 357 kJ/mol cured sheet form. fiber filler is fiberglass mat, as well thermomechanical (TMA) slight dependence mat direction measured properties.