the Institute of Space and Aeronautical Science University of Tokyo
the Institute of Space and Aeronautical Science University of Tokyo
出版者
東京大学宇宙航空研究所
雑誌名
東京大学宇宙航空研究所報告
巻
2
号
2_B
ページ
738 - 755
発行年
1966-06
抄録（英）
The mechanical properties of solid propellants are very important from the viewpoint of mechanical failure and osillatory burning which are some of causes of abnormal burning or explosion of rocket motors. This paper describes the experimental results of a series of mechanical tests for the following purposes: (1) to investigate the necessary mechanical properties which should be provided for the rocket grains based on the stress and strain analyses under high internal pressure. (2) to make clear the various kinds of effects on the mechanical properties so as to be useful in design and in estimating the strength under such complicated loading conditions as launching and burning. (3) to get the fundamental data for establishing the specifications or test procedures in master sample tests prior to launching and for giving the qualification as rocket propellants. The various kinds of effects such as loading rate, specimen size, location in cast propellants, temperature and humidity on the mechanical properties are clarified by carrying out tensile and compressive tests. Furthermore, the values of Poisson's ratio in function of stress and the correlations among the various mechanical properties are discussed.
II.3.7 ポリウレタン固体推進剤の力学的物性について(3 推進剤)(II.関連研究)
SA0124892.pdf
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