日本航空宇宙学会論文集
Online ISSN : 2432-3691
Print ISSN : 1344-6460
ISSN-L : 1344-6460
論文
酸化剤流旋回型ハイブリッドロケットエンジン性能 パラメータの時刻変化予測
白石 紀子湯浅 三郎
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ジャーナル フリー

2013 年 61 巻 2 号 p. 31-37

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For hybrid rocket engines, there are some unique relationships between the parameters, such as the fuel regression rate, oxidizer mass flow rate, equivalence ratio and so on, which determine the burning properties. These relationships are strongly related to the engine performance. Our final goal of this study is to establish the optimum design method which considers the engine performance of hybrid rocket engines for practical hybrid rockets varying with time. In this paper, we focused on the time variation of ballistic parameters of the swirling-oxidizer-flow-type hybrid rocket engine. We establish the new simulation method, the Two-Step combustion model, in which at the fuel grain head the fuel regression rate is independent of the oxygen mass flux and in the rear region depends on the flux according to the ordinary hybrid combustion formula. The model succeeded to predict the time variation of the burning properties and ballistics parameters, which coincided with the experimental burning values and time behavior. These results show the possibility that there are two different combustion mechanisms in the burning process of the swirling-oxidizer-flow-type hybrid rocket engine.

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© 2013 The Japan Society for Aeronautical and Space Sciences
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