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Study of Combustion Characteristics of Hybrid Rocket Engine with Swirling Liquid Oxygen Flow and its Application to Small Sounding Rocket Engine

旋流液氧流混合火箭发动机燃烧特性研究及其在小声火箭发动机中的应用

基本信息

批准号：
14350513
负责人：
YUASA Saburo
金额：
$ 9.22万
依托单位：
Tokyo Metropolitan Institute of Technology
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (B)
财政年份：
2002
资助国家：
日本
起止时间：
2002 至 2004
项目状态：
已结题

项目摘要

By applying swirl to an oxidizer flow, our hybrid rocket engine with GO_2 and PMMA could obtain the high performance. In 2001, we launched the first hybrid rocket of 1.8m in length, which recorded the first successful flight of a hybrid rocket, in Japan. As the next stage, a hybrid rocket engine system with a swirling LOX flow was constructed. In order to investigate combustion processes of directly exposed PMMA to LOX, tests of a small hybrid combustor with a single port filled with LOX or GOX without swirling were carried out. It was found that a LOX layer appeared on the wall and combustion processes of LOX/PMMA are determined by evaporation of LOX.Experiments of combustion in a hybrid rocket engine with a swirling LOX flow showed that fuel regression rate, C^* efficiency and Isp of the hybrid rocket engine with the swirling LOX flow were smaller than those with the swirling GOX flow, resulting in lower performance of the hybrid rocket engine with LOX than that with GOX. The existen … More ce of a LOX layer on the combustion chamber wall decreased the combustion characteristics due to the loss of the angular momentum, the decrease of the net Go and the longer combustion time. Combustion oscillation called a "Chugging" mode also occurred.To improve the poor combustion performance, a regenerative-cooling nozzle of the hybrid rocket engine using LOX was adopted. Thermal analysis of the nozzle was performed, and a longitudinal channel-wall type regenerative-cooling nozzle with LOX was made. Vaporization experiments with LOX as the coolant, in which the mass flow rates of the oxygen used for combustion of the hybrid rocket engine and LOX passing through the nozzle were independently supplied to examine vaporization conditions of LOX, were conducted. It was confirmed that LOX was safely vaporized through the nozzle.A 1500-N thrust hybrid rocket engine was made. The burning test using GO2 was carried out and showed good performance. The future issue to achieve this project purpose is to match the regenerative-cooling LOX nozzle with the swirling oxygen type hybrid rocket engine for a sounding rocket. Less

通过在氧化剂流动中应用涡流，我们的GO_2和PMMA混合火箭发动机可以获得高性能。2001年，我们在日本发射了第一枚1.8米长的混合火箭，这是混合火箭首次成功飞行。作为下一阶段，构建了具有旋流液氧流动的混合火箭发动机系统。为了研究PMMA直接暴露在液氧中的燃烧过程，在一台单孔充气LOX或GOX的小型混合燃烧室上进行了无旋流燃烧试验。在旋流液氧混合火箭发动机上进行的燃烧试验表明，旋流液氧流混合火箭发动机的燃料后退率、C^*效率和ISP值均小于旋流液氧流混合火箭发动机的燃料退化率、C^*效率和ISP值，导致液氧混合火箭发动机的性能较低。The Existen…由于角动量的损失、净GO的减少和燃烧时间的延长，燃烧室壁上LOX层中Ce的增多降低了燃烧特性。为了改善燃烧性能差的问题，采用了液氧燃烧的蓄热式冷却喷管。对喷嘴进行了热分析，制作了带液氧的纵向通道壁式回热冷却喷嘴。进行了以液氧为冷却剂的雾化实验，分别提供混合火箭发动机燃烧用氧的质量流量和通过喷管的液氧的质量流量，以考察液氧的蒸发条件。确认液氧通过喷管安全汽化。研制了一台1500-N推力混合火箭发动机。进行了燃用GO2的燃烧试验，表现出良好的燃烧性能。为了实现这一项目目的，未来的课题是将回热冷却液氧喷管与探空火箭的旋流氧气型混合火箭发动机相匹配。较少