空气动力学学报2011，Vol.29Issue(6)：697-701,5.
脉冲爆震火箭发动机和小推力液体火箭发动机的性能对比分析
Performance comparison of pulse detonation rocket engine and liquid rocket engine with small thrust
摘要
Abstract
In order to find out the performance advantage of pulse detonation rocket engine over a rocket engine, the primary objective of this research is to compare the thrust and the specific impulse of PDRE based on constant-vol ume cycle model with a rocket engine with small thrust. The results show that at vacuum conditions, with the increas ing of initial temperature, the specific impulse increase not obviously. If the propellants are same and the sizes are similar, the thrust of PDRE is 3. 0 ~6. 8 times more than that of a liquid rocket engine's, while the specific impulses are equivalent.关键词
脉冲爆震火箭发动机/小推力液体火箭发动机/等容循环模型/性能Key words
pulse detonation rocket engine ( PDRE) / a liquid rocket engine with small thrust/ constant-volume cycle model/ performance分类
航空航天引用本文复制引用
穆杨,范玮,严宇,严传俊..脉冲爆震火箭发动机和小推力液体火箭发动机的性能对比分析[J].空气动力学学报,2011,29(6):697-701,5.基金项目
国家自然科学基金(50976094) （50976094）
教育部博士点基金项目(20096102110022) （20096102110022）
两工大基础研究基金(CJ201035) （CJ201035）
