|
| Thermal Decomposition Rule of a Four Component Composite Propellant |
| Revised:May 25, 2019 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/ issn.1672-9242.2019.05.000 |
| KeyWord:propellant thermal decomposition property thermal analysis kinetics reaction activation energy |
| Author | Institution |
| HUANG Wei-jia |
1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang , China;2. Special Service Research Institute, Shijiazhuang , China |
| CHEN Ming-hua |
1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang , China;2. Special Service Research Institute, Shijiazhuang , China |
| AN Zhen-tao |
1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang , China;2. Special Service Research Institute, Shijiazhuang , China |
| JIANG Zhi-bao |
1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang , China;2. Special Service Research Institute, Shijiazhuang , China |
|
| Hits: |
| Download times: |
| Abstract: |
| Objective To study the thermal decomposition characteristics of a four component propellant. Methods Differential scanning calorimetry (DSC) and thermogravimetric analysis (TG) experiments were carried out. Results DSC and TG curves of the propellant at different temperatures, as well as the DSC and TG curves of single propellant component at the same temperature were obtained, and the kinetic parameters of the reaction were calculated at different heating rates. Conclusion The thermal weight loss of the propellant is mainly divided into three stages. The range of 150~220 ℃ is mainly thermal decomposition of RDX, the range of 220~375 ℃ is mainly AP thermal decomposition, and the range of 375~515 ℃ is mainly the pyrolysis decomposition of AP and the decomposition of rubber. At the same time, the propellant has an exothermic peak at 200~237 ℃ and 337~385 ℃, and an endothermic peak at 240~248 ℃. The absorption peak of the propellant is the absorption peak of the AP crystal transition in the propellant, and the two exothermic peaks in the propellant are produced by the RDX thermal decomposition and the high temperature decomposition of the AP. At the same time, the activation energy of the propellant samples is calculated. The apparent activation energy of the propellant is in the range of 1.6×105~2.1×105 J/mol. With the thermal decomposition, the activation energy decreased first and then increased. |
| Close |
|
|
|