脉冲爆震火箭发动机的原理性试验

推进技术 ›› 2004, Vol. 25 ›› Issue (5): 450-453.

脉冲爆震火箭发动机的原理性试验

李强,张群,范玮,严传俊

西北工业大学动力与能源学院陕西西安710072;西北工业大学动力与能源学院陕西西安710072;西北工业大学动力与能源学院陕西西安710072;西北工业大学动力与能源学院陕西西安710072

发布日期:2021-08-15
基金资助:
国家自然科学基金(50106012;50336030);教育部优秀青年教师资助计划;西北工业大学毕业设计重点扶持项目的资助。

An experimental study for pulse detonation rocket engine

School of Power and Energy,Northwestern Polytechnic Univ., Xi’an 710072, China;School of Power and Energy,Northwestern Polytechnic Univ., Xi’an 710072, China;School of Power and Energy,Northwestern Polytechnic Univ., Xi’an 710072, China;School of Power and Energy,Northwestern Polytechnic Univ., Xi’an 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 阐述了脉冲爆震火箭发动机(PDRE)性能特点、结构和工作过程。采用航空煤油为燃料,氧气和压缩空气为氧化剂,分别进行了两相脉冲爆震火箭发动机原理性试验,所测得的爆震波压力接近充分发展的理想爆震波压力,说明采用煤油作为脉冲爆震火箭发动机的燃料是可行的。

关键词: 脉动式喷气发动机;燃料性能;爆震波试验+

Abstract: The performance characteristics, structure and working cycle of pulse detonation rocket engine (PDRE) were introduced firstly.Then using kerosene as fuel, oxygen and compressed air as oxidizers,proof-of-principle experiments of PDRE were successfully conducted.The results show that the measured detonation wave pressures are close to theoretical values.It also indicate that using kerosene as the fuel of PDRE is feasible.

Key words: Pulse jet engine;Fuel performance;Detonation experiments~+

李强,张群,范玮,严传俊. 脉冲爆震火箭发动机的原理性试验[J]. 推进技术, 2004, 25(5): 450-453.