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<p>Recently, with the continuous development of aerospace engineering, propellants have higher energy requirements than before. Propellant is the source of power for solid rocket motors, and its ignition and combustion performance directly affect the flight speed of solid motors and so on. Compared with the components of traditional propellants, GAP/CL-20 propellant has a higher energy density, which provides a higher specific impulse for solid rocket motors. However, the ignition and combustion mechanisms of GAP/CL-20 propellant is poorly understood. Therefore, for GAP/CL-20 and AP/HTPB propellants, the thermal oxidation characteristics, the ignition process and combustion process are explored based synchronous thermal analyzer, ignition and combustion process experimental systems. The results of the study show that the high-energy additives GAP and CL-20 contribute to the decomposition of AP. In the ignition process, the ignition delay time of GAP/CL-20 propellant is smaller than that of the AP/HTPB propellant over the pressure range of 0.1&#xa0;MPa to 3.0&#xa0;MPa. And the burning surface expansion speed of the GAP/CL-20 propellant is higher than that of the AP/HTPB propellant. In the combustion process, as the pressure increases from 0.1&#xa0;MPa to 3.0&#xa0;MPa, the combustion temperature of GAP/CL-20 propellant rises from 1941.5&#xa0;°C to 2960.1&#xa0;°C. The pressure index of GAP/CL-20 propellant reaches 0.66 (0.1&#xa0;MPa-3.0&#xa0;MPa). GAP/CL-20 propellant has a higher flame burning intensity than AP/HTPB propellant under the same experimental pressure conditions. Microscopically, the AlO three-finger peak structure of the GAP/CL-20 propellant is captured during combustion, further illustrating its high energy. The results of this study should provide technical support for the application of high-energy propellants and design of solid rocket motors.</p>

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Comparative study of the thermal oxidation, ignition, and combustion process of GAP/CL-20 and AP/HTPB propellants

  • 期刊论文

  • 发表日期：

    2026年4月7日

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  • Zexu Li,
  • Jianzhong Liu,
  • Xueqin Liao,
  • Huanhuan Gao,
  • Peini Xie

摘要

Recently, with the continuous development of aerospace engineering, propellants have higher energy requirements than before. Propellant is the source of power for solid rocket motors, and its ignition and combustion performance directly affect the flight speed of solid motors and so on. Compared with the components of traditional propellants, GAP/CL-20 propellant has a higher energy density, which provides a higher specific impulse for solid rocket motors. However, the ignition and combustion mechanisms of GAP/CL-20 propellant is poorly understood. Therefore, for GAP/CL-20 and AP/HTPB propellants, the thermal oxidation characteristics, the ignition process and combustion process are explored based synchronous thermal analyzer, ignition and combustion process experimental systems. The results of the study show that the high-energy additives GAP and CL-20 contribute to the decomposition of AP. In the ignition process, the ignition delay time of GAP/CL-20 propellant is smaller than that of the AP/HTPB propellant over the pressure range of 0.1 MPa to 3.0 MPa. And the burning surface expansion speed of the GAP/CL-20 propellant is higher than that of the AP/HTPB propellant. In the combustion process, as the pressure increases from 0.1 MPa to 3.0 MPa, the combustion temperature of GAP/CL-20 propellant rises from 1941.5 °C to 2960.1 °C. The pressure index of GAP/CL-20 propellant reaches 0.66 (0.1 MPa-3.0 MPa). GAP/CL-20 propellant has a higher flame burning intensity than AP/HTPB propellant under the same experimental pressure conditions. Microscopically, the AlO three-finger peak structure of the GAP/CL-20 propellant is captured during combustion, further illustrating its high energy. The results of this study should provide technical support for the application of high-energy propellants and design of solid rocket motors.