固体火箭冲压发动机测控技术研究

【作者】 林禹；

【导师】 李进贤；

【作者基本信息】 西北工业大学 ， 航空宇航推进理论与工程， 2002， 硕士

【摘要】 我国发展中远程、高超声速固体冲压导弹已经启动，其关键技术之一是研制性能优良的固体火箭冲压发动机，而试验测控技术是发动机研制中不可或缺的重要基础。 本文在深入分析讨论固体火箭冲压发动机试验参数特点以及进气模拟对控制系统要求的基础上，提出了发动机温度、压力、流量及其推力测量的总体方案和进气模拟总体控制方案。利用LabVIEW测量与自动化软件开发平台，开发了适用固体火箭冲压发动机试验推力、压力、流量和温度测量的数据采集软件。基于PID控制器开发了温度、压力调节控制软件，能根据试验要求自动地调节空气和燃油的流量，实现进气温度、压力模拟和试验过程控制。开发了通用的温度、压力、流量、推力等物理量标定程序。并建立了相应的试验数据库。 利用本文建立的测控系统，进行了多次进气模拟试验研究。初步摸清了进气温度模拟和进气压力模拟的规律，实现了燃油流量和进气气流压力的自动控制。为固体火箭冲压发动机试验研究打下基础。更多还原

【Abstract】 The research project of the middle-long and hypersonic missile with solid rocket-ramjet engine has been launched. The measurement and control technologies are the important basis of developing engine, which is one of the key technologies of the research.Under the base of the parameter characteristics of the engine thermodynamics and the air-inlet simulation, the measurement and control schemes are designed with virtual instrument technology. The experimental data acquisition software, which can acquire temperature, pressure, flow rate, and thrust of the engine, is developed with LabVIEW software development platform. With PID, air-inlet simulation control software is programmed at the same time, which can control the total temperature and pressure of the air-inlet efficiently. In addition, the parameter calibration of the engine and the experimental database are accomplished.Air-inlet simulation experiment has been carried out, through which total temperature and pressure simulation rule has been made clear, and the auto control of the fuel rate and air pressure has been realized. All of the work made foundation of developing solid rocket-ramjet engine.更多还原