Abstract
New hydrogen-oxygen resonance igniter is designed to use in synchronistic multi-ignition for aero-spike nozzle engine. Ignition start time, delay time, repetition of multi-ignition and lifetime of igniter are tested. It can be found from performance tests that the new hydrogen-oxygen resonance igniter with quick starting, short time delay for ignition, good repetition and long life time. Two igniters are used in every synchronistic ignition tests. The pipeline s influence to synchronization is analyzed. Two ways are put forward for shorten the time difference of synchronistic. It can be concluded from total 5 times synchronistic ignition tests that the new hydrogen-oxygen resonance igniter can satisfy the requirements of synchronistic multi-ignition for aerospike nozzle engine and other liquid propellant rocket engines which need synchronistic multi-ignition.
| Original language | English |
|---|---|
| Pages (from-to) | 627-631 |
| Number of pages | 5 |
| Journal | Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics |
| Volume | 31 |
| Issue number | 6 |
| State | Published - Jun 2005 |
Keywords
- Ignition
- Liquid propellants
- Resonance
- Rocket engine
- Synchronization
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