II.3.8 固体推進剤の力学的物性と燃焼特性との関連について(3 推進剤)(II.関連研究)

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Whether the solid propellants burn favorably or not, depends on the charge design of rocket motor as well as on the chemical and mechanical properties of solid propellants. In this paper, the experimental results of burning tests of rocket motors are described and the correlation of mechanical properties of polyurethane-base solid propellants to the combustion characteristics are discussed, taking into account the various kinds of experimental results on the mechanical properties described in the previous paper. That is, the two kinds of tentative or empirical criteria are presented with the intention of forecasting the burning results to certain extent by only the mechanical properties and the configuration of rocket grains which seem to be closely related with the burning characteristics. These two criteria correspond to the two kinds of abnormal burning or explosion of rocket motors due to the high internal pressure resulting from the mechanical failure and osillatory burning. Tensile strength, elongation to rupture and Young's modulus in compression are used as the representative mechanical properties and the restriction factor is used as the configuration of rocket grain. The three small sounding rockets (HT-110-1, 2, 3) were launched successfully after confirming that the mechanical properties of solid propellants were beyond the two kinds of critical values. It seems that such an attempt is one of useful ways to predict the burning results, if other conditions are kept good.
宇宙航空研究開発機構の論文

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植村益次
東京大学宇宙航空所究所

II.3.8 固体推進剤の力学的物性と燃焼特性との関連について(3 推進剤)(II.関連研究)

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