【作者】 蒋波；

【导师】 严传俊；

【作者基本信息】 西北工业大学 ， 航空宇航推进理论与工程， 2007， 硕士

【摘要】 脉冲爆震发动机是一种利用脉冲式爆震波产生推力的新概念发动机。由于它有很多优点，在航空、航天领域具有广阔的的应用前景。为了将脉冲爆震发动机从实验室研究推向工程应用，本项目进行了脉冲爆震发动机模拟发射试验。脉冲爆震发动机模拟发射试验系统由火箭式脉冲爆震发动机和发射导轨架组成。火箭式脉冲爆震发动机主要包括爆震管、点火器、气路与油路及控制元件。爆震管内径为80mm，管内设置了增强由爆燃向爆震转变的螺旋件；发动机控制元件应用可编程器PLC控制其点火及工作时序；设计了可以外接气路或自带气瓶供给的气路通道和提供燃油供给的油路通道。导轨架体系包括架体和承载小车，发动机置于小车上在导轨上运动。 按供气方式的不同，试验分为两种情况，一是发动机接实验室气源时的工作情况，二是发动机自带气瓶时的点火情况。接实验室气源时，对发动机推力及压力信号作了测量，用两种方法测试了发动机的推力，一是将发动机放置在实验台架上，通过推力传感器测试了平均推力和管内爆震压力；二是利用高速摄影记录了发动机在导轨上的运动情况(包括位移、速度和加速度)，通过牛顿运动定律得出平均推力并计算了有效比冲。发动机自带气瓶时，测量了减压器在一定出口压力下的气瓶放气流量，由于气瓶供气量小且不稳定，设计了控制变频点火和间歇性供油供气的PLC程序，用高速摄影测量了初始频率爆震下的发动机运动量，计算了有效比冲。 试验结果表明了火箭式脉冲爆震发动机在一定的工作频率下能够产生有效推力，达到稳定的工作状况，该项试验对于脉冲爆震发动机的工程应用有一定启示作用。更多还原

【Abstract】 Pulse detonation engine(PDE) is a new concept of propulsion system which uses pulse detonation waves to produce thrust. Due to its obvious advantages PDE has wide applications in aeronautical and astronautical area. In order to promote PDE research from laboratory level to engineering applications, this study conducted simulation test of PDE flight test. The test system consisted of a pulse detonation rocket and a launcher. The pulse detonation rocket contained a pulse detonation tube, pulse ignition device, supplies of air and fuel and a controller. The detonation tube had inner diameter of 8mm and Shchelkin spirals for speeding up deflagration to detonation transition. The PDE controller was a programmable logic controller(PLC) which controlled ignition frequency and PDE working time sequence. The manifold for air and fuel supplies was designed and manufactured. The air came from laboratory supply or compressed air bottle. The launcher was made up of a track frame and a barrow. The PDE system can move freely on the track.Since the volume of compressed air bottle was limited, the first step test used air from laboratory air supply and the PDE thrust and detonation pressure were measured. Two methods for thrust measurement are adopted. The first method employed thrust sensor to measure its averaged thrust. The second method used a high-speed camera(HSC) to measure PDE’s displacement, speed and acceleration from which PDE thrust and specific impulse can be deduced. The second step test utilized air from compressed air bottle. Since bottle volume was small and the flow was unsteady, the ignition frequency and intermittent supply of air and fuel were controlled by PLC. The PDE motion parameters were recorded by HSC ands its specific impulse was obtained by data processing.The experiments showed that the PDE can produce effective thrust under certain detonation frequency and its operation was stable. This study will bring important heuristics for PDE’s applications.更多还原