Research on gas-dynamic resonance igniter for simultaneous multi-ignition of hydrogen-oxygen rocket engine
- Paper number
IAC-06-C4.P.3.07
- Author
Dr. Nanjia Yu, Beijing University of Aeronautics and Astronautics, China
- Coauthor
Prof. Guobiao Cai, Beijing University of Aeronautics and Astronautics, China
- Year
2006
- Abstract
In order to research the hydrogen-oxygen aerospike nozzle rocket engine which may be used on SSTO reusable launch vehicle, the simultaneous multi-ignition of hydrogen-oxygen igniter is the one of its key technologies. Six schemes of hydrogen-oxygen igniter for multi-chamber simultaneous multi-ignition are provided and expound and prove, multi small coaxial hydrogen-oxygen resonant igniter assemble scheme is selected. Structure parameters and pressure of small coaxial hydrogen-oxygen resonant igniter are obtained from more than 600 times foundation experiments of resonance heating. The ignition tests showed that small coaxial hydrogen-oxygen resonant igniter is characterized with advantages of repeatedly multi-ignition performance and high reliability. The shortest start time 0.17s is reached. The simultaneous ignition time different of three igniter is shorter than 0.01s. The ignition delay time repeatability of every igniter are good, even placed igniter in different position of ignition system. It is concluded from ignition tests that multi-small coaxial hydrogen-oxygen resonant igniter assemble is a good ignition scheme for aerospike nozzle engine which need multi-chamber simultaneous multi-ignition.
- Abstract document
- Manuscript document
IAC-06-C4.P.3.07.pdf (🔒 authorized access only).
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