Composite Solid Rocket Propellant Based on GAP Polyurethane Matrix with Different Binder Contents

• 作 者: Islam K .Boshra Ahmed Elbeih GUO Lin Mohamed G .Zaki
• 机 构: School of Chemistry and Environment ,Beihang University ,Beijing 100191 ,China“,”Military Technical
• 出 处: 火炸药学报
• 发表日期: 2020年4期
• 关键词: physical chemistry glycidyl azide polymer (GAP) hydroxyl terminated polybutadien

Different GAP-based CSRP samples with different binder contents were prepared and compared with that of conven-tional HTPB propellant .The crosslinker mixture of trimethylol propane (TMP) and butane diol (BD) was used in the GAP ma-trix beside the addition of dibutyltin dilaurate (DBTDL ) to ensure cross-linking and curing completion of the prepared CSRP .The viscosity and hardness of al prepared formulations were monitored continuously during the curing process .The mechanical char-acteristics of cured samples were tested .The bing rate at operating pressure and specific impulse were measured ,while the theoretical specific impulse ( Isp ) was calculated by ICT code and compared with the measured results .According to the re-sults ,DOA was found to be a suitable plasticizer for GAP when using in propellant .The mechanical properties of CSRP with 25％ GAP can produce the optimum mechanical behavior ,which is close to that of HTPB-based CSRP .The optimum GAP-based formulation is one candidate to replace the traditional HTPB-based CSRP with high bing rate for some applications .