2.4m跨声速风洞TPS测控系统设计与实现  

Design and realization of TPS measurement and control system for 2.4m transonic wind tunnel

作　　者：芮伟[1] 易凡[1] 杜宁[1] 秦建华[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2008年第4期72-75,共4页Journal of Experiments in Fluid Mechanics

摘　　要：带涡轮动力模拟器(TPS)实验是一种先进的进/排气一体化动力模拟实验技术,该技术能为大型军用运输机、战略轰炸机、大型民用飞机、巡航导弹等推进/机体一体化设计提供必须的实验平台和有力的技术支撑。其中,TPS测控系统主要是为TPS单元驱动气体流量提供精确控制和测量并且负责TPS单元的安全监控工作。笔者介绍了2.4m跨声速风洞TPS测控系统的设计、实现以及调试应用情况。结果表明,整个实验系统运行稳定,工作可靠,TPS涡轮驱动气体的流量波动可以控制在0.001kg/s以内,可应用于型号实验。The advanced testing technique with turbine powered simulator（TPS） to simulate the aerodynamic effects of aircraft＇s propulsion system can provide essential testing setup and strong technical support for the propulsion/airframe integration design of large-scale military aircraft, strategy bomber, large-scale civil air- craft and cruise missile. The measurement and control system of TPS supplies steady driving air and supervises health of TPS units. The design, realization and debug of TPS measurement and control system in the 2.4m transonic wind tunnel is introduced and the results show that the whole system is stable, reliable, the mass flow control accuracy of TPS driving air is within 0.001kg/s, the TPS measurement and control system of the 2.4m transonic wind tunnel can be used to develop the aircrafts.

关 键 词：跨声速风洞 涡轮动力模拟器 安全监控系统 流量控制系统 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]