| 摘要: |
| 在环形喷嘴气动谐振加热的试验研究基础上,对同轴氢氧谐振点火器进行了点火性能试验和反压试验研究,结果表明:点火器能为液体火箭发动机可靠点火提供强大热流;能重复多次点火,寿命长;点火器抗系统干扰能力强,点火器出口反压快速增长时,点火器不会熄火,仍能持续提供稳定的氢氧火炬。非电钝感的同轴氢氧谐振点火器可作为正在研究发展中的可重复使用液体火箭发动机多次点火的优选方案之一。 |
| 关键词: 液体推进剂火箭发动机 点火器 点火试验 性能测试 |
| DOI： |
| 分类号:V43424 |
| 基金项目:国家"八六三"项目(863 2 3 4 10(4);863 2 3 4 7);航天科技创新基金2000年资助项目。 |
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| Experimental investigation for coaxial hydrogen/oxygen resonance ignitor |
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YU Nan-jia, ZHANG Guo-zhou, SONG Ya-na, MA Bin, TONG Xiao-yan
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School of Astronautics,Beijing Univ. of Aeronautics and Astronautics,Beijing 100083,China
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| Abstract: |
| Gas-dynamic resonance heating tests for coaxial ring injector are performed for investigating coaxial hydrogen/oxygen resonance ignitor to validate the performance of resonance ignitor.It can be concluded from experiments that resonance ignitor can supply steady strong torch for liquid rocket engine ignition,multi-ignition,and with long life-span. The ignitor can work reliably when inlet pressure of hydrogen and oxygen changed and even when back pressure rise up quickly. Coaxial hydrogen/oxygen resonance ignitor is non-electric and bluntly sensible,which is good ignition scheme for the developing reusable liquid rocket engine. |
| Key words: Liquid propellant rocket engine Igniter Ignition test Performance testing |
