Testing and Modeling of a Porous Polyethylene Axial-Injection, End-Burning Hybrid Rocket Motor
Testing and Modeling of a Porous Polyethylene Axial-Injection, End-Burning Hybrid Rocket Motor
复制标题
多孔聚乙烯轴向喷射、端燃式混合火箭发动机的测试和建模
DOI：
10.2514/6.2015-4038
复制
发表时间：
2015
影响因子：
1.9
通讯作者：
R. Frederick
中科院分区：
文献类型：
--
作者：
M. Hitt;R. Frederick
允许气态氧化剂通过多孔固体燃料最近被引入，作为一种增加混合火箭燃烧速度的方法。本文详细介绍了多孔轴向喷射末燃混合火箭发动机燃料回归率的实验和分析研究结果，以了解燃料回归率背后的物理原理。以聚乙烯为多孔燃料，气态氧为氧化剂进行了试验。使用100微米、50微米和15微米的孔径对标称试样进行测试。测试压力范围从大气压到1194千帕，氧化剂喷射速度范围从35米/秒到80米/秒。回归率是通过测试前和测试后固体燃料的长度测量来确定的。实验结果表明，多孔轴喷末燃混合气的回归速率是燃烧室压力的函数，而不是传统混合气中典型的氧化剂质量通量。回归速率从大气压下的约0.65 mm/s到1194 kPa下的7.74 mm/s不等。该分析模型是在一个标准烧蚀模型的基础上建立的，该模型经过修改，包括氧化剂在晶粒中的流动。从火焰的传热主要是使用一个经验确定的火焰系数，包括所有的传热机制在一个术语建模。在固体火箭发动机颗粒扩散火焰模型的基础上，建立了探索性火焰模型，并与经验火焰系数进行了比较。GDF模型与实验结果吻合，表明GDF模型具有深入研究多孔轴向喷射末燃混合火箭发动机火焰结构的潜力。
Allowing a gaseous oxidizer to pass through a porous solid fuel has recently been introduced as a way to increase the burning rate of hybrid rockets. This paper details the results of an experimental and analytical investigation into the regression rate of a porous axial-injection, end-burning hybrid rocket motor to understand the physics behind the fuel regression rate. Testing was conducted using polyethylene as the porous fuel and gaseous oxygen as the oxidizer. Nominal test articles were tested using 100 micron, 50 micron, and 15 micron pore sizes. Pressures tested ranged from atmospheric to 1194 kPa, and oxidizer injection velocities ranged from 35 m/s to 80 m/s. Regression rates were determined using pretest and posttest length measurements of the solid fuel. Experimental results demonstrated that the regression rate of the porous axial-injection, end-burning hybrid was a function of the chamber pressure as opposed to the oxidizer mass flux typical in conventional hybrids. Regression rates ranged from approximately 0.65 mm/s at atmospheric pressure to 7.74 mm/s at 1194 kPa. The analytical model was developed based on a standard ablative model modified to include oxidizer flow through the grain. The heat transfer from the flame was primarily modeled using an empirically determined flame coefficient that included all heat transfer mechanisms in one term. An exploratory flame model based on the Granular Diffusion Flame model used for solid rocket motors was also adapted for comparison with the empirical flame coefficient. The GDF model showed agreement with the experimental results indicating that the GDF model has potential for giving insight into the flame structure in a porous axial-injection, end burning hybrid rocket motor.
狭窄固体燃料管道中火焰传播的新结构
DOI：
--
发表时间：
2010
期刊：
影响因子：
--
作者：
菅野陽将;黒田一幸;Mizuho Sato;Naotaka Izuo;佐藤瑞穂;Mizuho Sato;佐藤瑞穂;佐藤瑞穂;佐藤瑞穂;佐藤瑞穂;浅井 雅;浅井 雅;浅井 雅;浅井 雅;浅井 雅;浅井 雅;Tsuneyoshi Matsuoka;松岡常吉;松岡常吉;Tsuneyoshi Matsuoka;Tsuneyoshi Matsuoka
通讯作者：
Tsuneyoshi Matsuoka