The thermal decomposition kinetics of composite modified double-base （CMDB） propellants with a series of contents of hexogeon （RDX） was investigated by using parameters of Tco, Ti, Tp, Tf, Tb, Ta, E, lg A and AH, ...The thermal decomposition kinetics of composite modified double-base （CMDB） propellants with a series of contents of hexogeon （RDX） was investigated by using parameters of Tco, Ti, Tp, Tf, Tb, Ta, E, lg A and AH, which were obtained from using a CDR-4P differential scanning calorimeter （DSC） and Perkin-Elmer Pyris l thermogravimetric analyzer （TG） analyses with heating rates of 5, 10, 15 and 20 K/min. Reliable activation energy was calculated using Flynn-Wall-Ozawa method before analyzing the thermal decomposition mechanism. TG-DTG curves were treated with Malek method in order to obtain the reaction mechanisms. The obtained results show that the thermal decomposition mechanisms with the conversion from 0.2 to 0.4 was f（a）= 1/2a, and with the conversion from 0.5 to 0.7 was f（a）=（1/4）（1--a）[--1n（1 --a）]-3.展开更多
文摘The thermal decomposition kinetics of composite modified double-base （CMDB） propellants with a series of contents of hexogeon （RDX） was investigated by using parameters of Tco, Ti, Tp, Tf, Tb, Ta, E, lg A and AH, which were obtained from using a CDR-4P differential scanning calorimeter （DSC） and Perkin-Elmer Pyris l thermogravimetric analyzer （TG） analyses with heating rates of 5, 10, 15 and 20 K/min. Reliable activation energy was calculated using Flynn-Wall-Ozawa method before analyzing the thermal decomposition mechanism. TG-DTG curves were treated with Malek method in order to obtain the reaction mechanisms. The obtained results show that the thermal decomposition mechanisms with the conversion from 0.2 to 0.4 was f（a）= 1/2a, and with the conversion from 0.5 to 0.7 was f（a）=（1/4）（1--a）[--1n（1 --a）]-3.
