| タイトル | Study of the thermal degradation mechanism of a composite propellant |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750019097 |
| 著者（英） | Schmidt, W. G. |
| 著者所属（英） | Jet Propulsion Lab., California Inst. of Tech.|Aerojet Solid Propulsion Co. |
| 発行日 | 1975-05-01 |
| 言語 | eng |
| 内容記述 | The current experimental program was designed to systematically investigate the role of the oxidizer in the thermal degradation process of composite propellants. The scanning electron microscope (SEM) was used to examine the failure sites in thermally degraded propellant samples. The formulation variables tested were oxidizer purity, oxidizer particle size, and oxidizer to binder bonding agent. The binder, a saturated hydrocarbon, was kept constant throughout the experiments. The oxidizers were: AP, chlorate-doped AP, arsenate-doped AP, and phosphate-doped AP. The oxidizer particle size distribution was 60% of the large fraction and 40% of the small fraction. The bonding agent, when present, was used at the 0.15% level. The data showed that both the oxidizer purity and particle size had an important affect on the thermal degradation process. The affect of the oxidizer particle size was more noticeable at the higher temperature and stress levels. An examination of the failure site, by SEM, of propellants subject to these latter conditions indicated that the fracturing of the large oxidizer particles led to the propellant cracking. |
| NASA分類 | PROPELLANTS AND FUELS |
| レポートNO | 75N27169
REPT-1196-81F
NASA-CR-143142 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/189453 |
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