摘要
简要介绍了超声速自由射流高空模拟和试验技术,分析了超声速自由射流马赫数控制的原理,给出了控制方式及建立多输入多输出马赫数控制系统的方法。设计并实现了基于单支点半柔性壁超声速自由射流喷管,及双电动缸同步伺服控制技术的超声速自由射流马赫数控制系统。吹风试验结果表明,采用的双电动缸同步伺服控制技术,可对单支点半柔性壁超声速自由射流喷管柔性壁面实现同步控制,即精确控制超声速自由射流喉道面积;同时,该控制系统还可连续、有效地控制超声速自由射流马赫数。
The supersonic free-jet attitude simulation and test technologies were introduced briefly. The theory about Mach number control for supersonic free-jet was analyzed, and the designing of multi-input multi-output （MIMO） Mach number control system was given. At last, the control system was designed and realized based on single-back half-flexible free-jet nozzle and dual-electric-cylinder synch servo control technology. The test results indicate that the flexible wall of single-back half-flexible free-jet nozzle can be controlled synchronized by dual-electric-cylinder synchronized servo control technology, i.e. the throat area of supersonic free-jet can be controlled precisely; at the same time, the Mach number can be controlled effectively and continually.
出处
《燃气涡轮试验与研究》
北大核心
2015年第4期45-48,共4页
Gas Turbine Experiment and Research
关键词
超声速自由射流
高空模拟试车台
高空模拟试验
喉道面积
马赫数控制系统
同步控制
supersonic free-jet
altitude simulation test facility
altitude simulation test
throat area
Mach number control system
synch control
