| 黄伟佳,陈明华,安振涛,姜志保.某四组元复合推进剂的热分解规律研究[J].装备环境工程,2019,16(5):55-58. HUANG Wei-jia,CHEN Ming-hua,AN Zhen-tao,JIANG Zhi-bao.Thermal Decomposition Rule of a Four Component Composite Propellant[J].Equipment Environmental Engineering,2019,16(5):55-58. |
| 某四组元复合推进剂的热分解规律研究 |
| Thermal Decomposition Rule of a Four Component Composite Propellant |
| 修订日期：2019-05-25 |
| DOI：10.7643/ issn.1672-9242.2019.05.000 |
| 中文关键词: 推进剂 热分解性能 热分析动力学 反应活化能 |
| 英文关键词:propellant thermal decomposition property thermal analysis kinetics reaction activation energy |
| 基金项目: |
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| Author | Institution |
| HUANG Wei-jia | 1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang 050003, China;2. Special Service Research Institute, Shijiazhuang 050000, China |
| CHEN Ming-hua | 1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang 050003, China;2. Special Service Research Institute, Shijiazhuang 050000, China |
| AN Zhen-tao | 1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang 050003, China;2. Special Service Research Institute, Shijiazhuang 050000, China |
| JIANG Zhi-bao | 1. Department of Ammunition Engineering of Army Engineering University, Shijiazhuang 050003, China;2. Special Service Research Institute, Shijiazhuang 050000, China |
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| 中文摘要: |
| 目的 研究某四组元推进剂的热分解特性。方法 进行差示扫描量热（DSC）和热重分析（TG）实验。结果 分别得到了推进剂在不同温度下的DSC和TG曲线，以及同一温度下推进剂各单组分的DSC和TG曲线，并计算得到了不同升温速率下的反应动力学参数。结论 推进剂的热失重主要分为三个阶段，150～220 ℃的范围主要为RDX的热分解，220~375 ℃的范围主要为AP热分解，375~515 ℃的范围主要为部分AP高温分解和橡胶分解。同时推进剂在200~237 ℃和337~385 ℃各出现了一个放热峰，在240~248 ℃出一个吸热峰。推进剂的吸热峰为推进剂中AP晶型转变的吸热峰，推进剂中两个放热峰分别是由于RDX热分解和AP的高温分解产生的。同时计算得到推进剂样品的活化能，推进剂的表观活化能在1.6×105~2.1×105 J/mol的范围之间，随着热分解的进行，活化能先降低后升高。 |
| 英文摘要: |
| 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. |
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