脉冲爆震火箭发动机模拟运动的初步探索性实验研究  

Preliminary Exploration in Experimentally Studying Simulated Motion of PDRE(Pulse Detonation Rocket Engine) System

作　　者：蒋波[1] 严传俊[1] 黄希桥[1] 李牧[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2008年第3期368-372,共5页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(50336030)资助

摘　　要：实验进行了火箭式脉冲爆震发动机系统在发射架上的模拟运动,发动机以汽油为燃料、压缩空气为氧化剂,并由自行研制的带有PLC可编程控制器装置控制发动机的点火频率和油气供给。对发动机系统运动模型做了实验研究,用高速摄影机测量了脉冲爆震发动机运动的位移并得到了发动机的冲量和比冲。Aim. In order to verify very preliminarily that the PDRE produces sufficient mrust performance, we constructed a simple PDRE system, which can simulate the motion of PDRE on a simple launcher whose angle can be adjusted. In the full paper, we explain in some detail our explorative simulation experiments and simulation results; in this abstract, we just add some pertinent remarks to listing the three topics of explanation. The first topic is ： the simple PDRE system constructed. In the first topic, Fig. 1 in the full paper shows the schematic of the constructed PDRE system. The second topic is. the fuel supply and control systems of PDRE. Its two subtopics are： the design of fuel supply system （subtopic 2.1） and the PLC （programmable logic controller） （subtopic 2.2）. In subtopic 2.1, Fig. 6 shows the variation of air flow at the outlet of the system＇s air pressured bottle with air pressure. In subtopic 2.2, we design our PLC to control ignition frequency, fuel and compressed air supplies and present Fig. 9 showing the design flow chart and PLC time sequence. The third topic is： the motion of PDRE system as recorded by a high-speed camera. In this topic, we use the high-speed camera to measure and then calculate the initial displacement and speed of the PDRE. Thus, we obtain the average thrust and specific impulse of PDRE as 69 N and 96 s respectively.

关 键 词：火箭发动机 脉冲爆震火箭发动机 PLC控制器 高速摄影 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]