端面燃焼式ハイブリッドロケットの基礎研究:その2 燃焼特性
端面燃焼式ハイブリッドロケットの基礎研究:その2 燃焼特性
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端燃式混合火箭基础研究：第二部分燃烧特性
DOI：
10.2322/jjsass.49.40
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发表时间：
2001
期刊：
影响因子：
--
通讯作者：
勲 工藤
中科院分区：
文献类型：
--
作者：
望 橋本;隆博 加藤;晴紀 永田;勲 工藤
为克服常规固液火箭发动机燃烧过程中O/F偏移造成比冲损失和燃烧效率低的缺点，提出了一种新的设计思路。这个被命名为“端燃混合火箭“的想法的要点是，氧化剂气体在多孔固体燃料床的差距空间中流动。在固体燃料床的末端形成扩散火焰。通过实验研究，阐明了该推进剂的基本燃烧特性。结果表明，相同当量比下的燃速压力指数约为0.85，与当量比基本无关。利用该结果，给出了端燃固液火箭发动机的设计方法。最后，推力和比冲估计为氧化剂气体流量的函数，以调查的节流特性的电动机。
To overcome defects of conventional hybrid rockets such as the loss of specific impulse, which is caused by the O/F shift during the combustion, and the low combustion efficiency, the authors have proposed a new idea of design. The point of this idea, named “End-Burning Hybrid Rocket, ” is that oxidizer gas flows in the gap space of a porous solid fuel bed. Diffusion flame is formed at the end of the solid fuel bed. Experimental studies were made to clarify the basic combustion characteristics of the propellant. Results show that pressure exponent of the burning rate with the same equivalence ratio is approximately 0.85 and virtually independent with the equivalence ratio. Using this result, a designing method of End-Burning Hybrid Rocket Motor is shown. Finally, thrust and specific impulse is estimated as functions of oxidizer gas flow rates to investigate the throttling characteristics of the motor.