超声速自由射流马赫数控制系统设计  

Design of supersonic free-jet Mach number control system

作　　者：乔彦平[1] 田金虎[1] 吴锋[1] 耿卫民[1] 

机构地区：[1]中国燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川江油621703

出　　处：《燃气涡轮试验与研究》2015年第4期45-48,共4页Gas Turbine Experiment and Research

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.

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 

分 类 号：V233.73[航空宇航科学与技术—航空宇航推进理论与工程]