双管脉冲爆震火箭发动机实验研究

Experimental Investigations on a Dual-Tube Pulse Detonation Rocket Engine

关键词:  脉冲爆震火箭发动机  煤油  氧气  传感器  频率  推力

Key words:  Pulse detonation rocket engine  Kerosene  Oxygen  Transducers  Frequency  Thrust

摘要:

为研究双管脉冲爆震火箭发动机共同工作的协同性,以航空煤油和氧气作为燃料和氧化剂,基于双管脉冲爆震火箭发动机系统进行了单管单独工作与双管同时工作的实验,工作频率范围为5~25Hz,对压力和推力的测量结果表明,双管同时工作对单管稳定工作几乎不会产生影响；推力测量数据显示,相同工况下,双管同时工作产生的推力与两单管单独工作产生的推力之和基本相等,无论单管还是双管,在5~15Hz频率范围内,平均推力基本上线性增加,在15~25Hz频率范围内,平均推力增加逐渐趋缓。 

Abstract:

To investigate operation of a dual-tube pulse detonation rocket engine (PDRE), experiments were carried out on a dual-tube PDRE system including with only one single-tube working and dual-tube working simultaneously, while operation frequency ranging from 5 to 25Hz. Aviation kerosene and oxygen were used as fuel and oxidizer, respectively. Pressure and thrust were measured by transducers. Experimental results show that, when working simultaneously, dual-tube has hardly any impact on the operation of either of the two single-tubes. In the same operating conditions, thrust data show that, whether single-tube or dual-tube, time-averaged thrust almost increases with operation frequency linearly between 5Hz and 15Hz. However, this trend slows down when operation frequency increases from 15 to 25Hz, and thrust of the dual-tube is nearly identical to that of the two single-tubes.