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| Temperature Dependence of the Specific Heat Capacity of Propellant |
| Received:July 15, 2015 Revised:December 15, 2015 |
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| DOI：10.7643/issn.1672-9242.2015.06.013 |
| KeyWord:propellant specific heat capacity DSC dynamic temperature modulation |
| Author | Institution |
| HU Zhe |
Ordnance Engineering College， Shijiazhuang ， China |
| JIANG Jin-yong |
Ordnance Technology Research Institute， Shijiazhuang ， China |
| LU Gui-e |
Ordnance Technology Research Institute， Shijiazhuang ， China |
| GE Qiang |
Ordnance Technology Research Institute， Shijiazhuang ， China |
| WANG Shao-guang |
Ordnance Technology Research Institute， Shijiazhuang ， China |
| JIA Hao-nan |
Ordnance Engineering College， Shijiazhuang ， China |
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| Abstract: |
| Objective To determine the specific heat capacity parameter of propellant. Methods 9/7 single-base propellant，SF-3 and GATo were selected as the research objects. The thermal decomposition characteristics of propellant were studied using thermogravimetric analyzer, and the experimental temperature zone of propellant was determined. The specific heat capacity of propellant in the temperature range was measured by the method of dynamic temperature modulation using DSC, and the changing law was analyzed for the specific heat capacity of propellant. Thermodynamic functions of propellant were calculated. Results The results showed that the specific heat capacity gradually increased with the rising temperature. Conclusion In the process of thermal simulation of propellant, from the safety point of view, the specific heat capacity of propellant at room temperature should be used. |
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