Preparation Optimization of CFRP and EPDM Composite by the Co-Curing Method

As the requirements of aerospace technology become more rigorous, the performance of solid rocket motor (SRM) cases needs to be further optimized. In the present study, a co-curing technique was used to fabricate carbon fiber reinforced polymer (CFRP)/ethylene-propylene-diene monomer (EPDM) composites whereby the properties of CFRP/EPDM composites were adjusted by varying the temperature, heating time and type of vulcanizing agent to obtain the optimum manufacturing process. The results of crosslink density (3.459 x 10(-4) mol/cm(3)) tested by nuclear magnetic resonance (NMR), a 90 degrees peel strength test (2.342 N/mm), and an interlaminar shear test (ILSS = 82.08 MPa) demonstrated that the optimum mechanical properties of composites were obtained under the temperature 160 degrees C heated for 20 min with the curing agent DCP/S. The interfacial phase and bonding mechanism of composites were investigated by scanning electron microscopy (SEM). Thermogravimetric analysis (TGA) further indicated that EPDM/DCP/S had favorable thermal stability. This will provide valuable recommendations for the optimization of the SRM shell preparation process.

Automated summary

In this study, a co-curing technique was utilized to optimize the properties of carbon fiber reinforced polymer/ethylene-propylene-diene monomer composites for solid rocket motor cases. Various parameters were adjusted to obtain the best manufacturing process. The results showed that the optimum mechanical properties were achieved at a temperature of 160 degrees C for 20 minutes with the curing agent DCP/S.