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Shijiazhuang, China

Jia H.-N.,Ordnance Engineering College | An Z.-T.,Ordnance Engineering College | Jiang J.-Y.,China Institute of Technology | Jia H.-D.,Unit 92207 | Xie Y.-L.,Unit 92207
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2015

To evaluate thermal decomposition behaviors and thermal hazard of the composite modified double base (CMDB) propellant with higher RDX content, a domestic developed CMDB propellant with approximate 50% RDX (named GHT-1A), was investigated by thermogravimetry (TG), differential scanning calorimetry (DSC), micro reaction calorimetry (μRC) and accelerating rate calorimetry (ARC). TG and DSC results show the exothermic decomposition process of GHT-1A can be divided into two stages. The values of the apparent activation energy (Ea) and pre-exponential constant (A) of the two stages are: Ea1=148.4 kJ mol-1, lgA1=14.8 s-1, and Ea2=175.1 kJ mol-1, lgA2=16.5 s-1. The chemical reaction mechanisms both obey the Avrami-Erofeev equation. The critical temperature of the thermal explosion of GHT-1A derived from DSC data is 212.0 ℃. The specific heat capacity of GHT-1A was determined by μRC. The calculation results show that the adiabatic time-to-explosion of GHT-1A is 22.7 min. ARC results reveal the adiabatic decomposition behaviors of GHT-1A, and a mass of adiabatic parameters were derived directly or by inertia factor modifying. The adiabatic time-to-explosion obtained by ARC is 8.9 min shorter than the front. TD24 estimated by adiabatic reaction kinetics is 120.8 ℃. Based on these results, the thermal hazard of the CMDB propellant with high content of RDX was analyzed preliminarily. ©, 2015, Journal of Solid Rocket Technology. All right reserved.

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