| アイテムタイプ |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
Evaluation of Ballistic Performance of Solid Propellants by Means of a Constant-Volume Bomb |
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言語 |
en |
| 言語 |
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言語 |
eng |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
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資源タイプ |
departmental bulletin paper |
| 著者 |
IWAMA, Akira
AOYAGI, Shoichiro
SOFUE, Teruo
YAMAZAKI, Kiroku
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| 出版者 |
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出版者 |
東京大学宇宙航空研究所 |
| 出版者（英） |
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出版者 |
Institute of Space and Aeronautical Science,University of Tokyo |
| 書誌情報 |
en : ISAS report/Institute of Space and Aeronautical Science,University of Tokyo
巻 32,
号 3,
p. 51-63,
発行日 1967-03
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
To obtain information quickly on the solid propellants under the laboratory-scale research, a method of the specific-impulse estimation by employing a ballistic bomb has been studied. Based on the maximum burning pressures of the liquid monopropellants is provided the covolume in a convenient form as a function of the loading density (⊿) alone with Noble-Abel equation of state, ρ(υ-α)=nRT. Thus, it becames possible to evaluate the impetus of propellant ((RT)/(m^^^-))_<ρ→0> without rendering extrapolation p→0 from the plots of ρ_<max> υ against the loading density, and the specific impulse can be derived. This method employing an approximation α=f(⊿) leads to identical results with performance data obtained according to Griffin's procedure, and is supported also by the fact that the same α vs. ⊿ relation can be applied to all the propellants mainly composed of carbon, hydrogen, oxygen, chlorine and nitrogen. Namely, by applying α=f(⊿) specified from a few selected propellants, the specific impulse is calculated for all the propellants of this type within experimental error throughout if some data of maximum burning pressures at high loading densities are obtained. Performance data of typical composite propellants are presented and compared to theoretical. With non-aluminized propellants measured values approach calculated, but there is a considerable discrepancy between these two values for aluminized propellants. The innappropriate assumption in the theoretical calculation and incomplete burning of aluminum particles seem to be the most likely cause of its discrepancy. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0372-1418 |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
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収録物識別子 |
AA00675986 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: SA2400545000 |
SA2400545.pdf (808.5 kB)
