摘要
通过对脉冲爆震火箭发动机（Pulse Detonation Rocket Engine，PDRE）气动阀，气动阀和雾化喷嘴一体化设计，进行改善燃油蒸发、掺混，改善点火性能，强化燃烧等关键技术的研究，研制一台内径58mm，长1300mm的PDRE原型样机。试验表明，该PDRE样机能产生稳定的间歇爆震波。根据混气充填速度的不同，以汽油/空气为推进剂的PDRE工作频率可以在25～40Hz内变化。试验对汽油／氧气为推进剂的PDRE进行研究，其工作频率可达10Hz。
Based on the investigation of the key technology including aero-valve,integration design of aero-valve and atomizer, the fuel vaporization and mixing,the improvement about ignition reliability and intensification of burning, a pulse detonation rocket engine prototype is designed, the diameter and the length of the engine are 58 mm and 1 300 mm. Using the gasoline/air as the propellant, the PDRE prototype can steadily and periodically operate at the frequencies of 25-40Hz under different mixture charging conditions. While using gasoline/oxygen as the propellant, the PDRE prototype can operate at the frequency up to 10Hz. The pressure time trace is recorded by four pressure transducers and the characteristic of the pressure wave is studied. The detonation can propagate in the combustor.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2006年第5期529-534,共6页
Journal of Nanjing University of Aeronautics & Astronautics
