【作者】 胡承启；

【导师】 范玮；

【作者基本信息】 西北工业大学 ， 人机与环境工程， 2007， 硕士

【摘要】 脉冲爆震火箭发动机是一种自带燃料和氧化剂，利用脉冲式爆震波产生高温、高压燃气来产生推力的新概念推进装置。由于脉冲爆震火箭发动机具有热循环效率高、结构简单、比冲大等优点，所以它将是21世纪一种极具潜力的航空航天飞行器动力装置。 本文在分析了两相脉冲爆震火箭发动机的工作原理及工作循环的基础上，建立了脉冲爆震火箭发动机的实验系统，系统包括：供油系统、供气系统、点火系统、推力测试台架、实验参数的数据采集与分析系统。进行了推力为120N多循环脉冲爆震火箭发动机模型的设计和实验。以煤油／氧气为燃料和氧化剂，在内径50mm、管长1.2m的爆震管(模型Ⅰ)或内径62mm、管长1.1m的爆震管(模型Ⅱ)上进行实验。首先进行的是不同头部结构、不同爆震室体积、不同当量比对推力和比冲的影响的实验，发现在不同的频率下，对于不同体积的爆震管，体积小的爆震管能够得到较高的推力与体积之比，在频率高时更加明显。在当量比0.5—1.7的范围之内，脉冲爆震火箭发动机的推力和比冲随当量比的增大而增大，即当量比的增加能够提升发动机的性能。接着对10种3类不同尾喷管进行实验，研究结果表明，各种喷管对性能均有提高；对每类喷管均存在一个最佳面积比，使推力增益最大；在受试的尾喷管中，收敛扩张喷管增益最大，达24％；填充系数对性能增益影响甚微。最后对电磁阀进行研究，进行了脉冲爆震火箭发动机提高频率的实验，将最高频率提升至25Hz。通过上述实验，找到了一些增加脉冲爆震火箭发动机推力及比冲的方法。更多还原

【Abstract】 Pulse detonation rocket engine （PDRE） is a new concept of propulsive device which takes fuel and oxidizer, utilizes high temperature and pressure gas produced by pulsed detonation wave to generate thrust. PDRE has great potential to become one of important propulsive devices of spacecraft in 21^st century because PDRE has many desirable advantages, including high thermodynamics cycle efficiency, simple configuration and high specific impulse.In this paper, the operation principle and working cycle of two-phase PDRE are analyzed firstly. The experimental system of PDRE is built up. It consists of fuel/oxygen supply system, ignition system, thrust testing stand system, engine parameter data acquisition and processing system. The multi-cycle PDRE model of 120N thrust was designed. Then on the tube of inner diameter 50mm, length 1.2m（model I） or the tube of inner diameter 62mm, length 1.1m（model II）, many experiments are performed using kerosene as fuel and oxygen as oxidizer. Firstly, the effect of thrust and specific impulse was performed on different head constructions, different volume of detonation tube, different equivalence ratio. With different volume tubes, the tube of small volume can get the higher thrust/volume. The experimental results indicated that the thrust and the specific impulse increase with the increase of the equivalence ratio under different equivalence ratio ranging from 0.5 to 1.7. It means that the increase of the equivalence ratio can increase the performance of PDRE. Then 10 nozzles from 3 typical types are chosen under experimental tests. The results show that all nozzles can augment the thrust of baseline PDE and there is an optimal nozzle area ratio where thrust augmentation is maximized. Amongst all tested nozzles, the maximal augmentation of 24% is attained by a convergent-divergent nozzle. Moreover, it is validated that fill-fraction has little effect on thrust augmentation. Finally, the experiment of high frequency was performed based on the research of solenoid valve. The highest frequency reached 25Hz.更多还原