暂冲式高速风洞连续变速压颤振试验流场控制系统研究  

Research on Flow Field Control System for Continuously Increasing Dynamic Pressure Flutter Test in Intermittent High-Speed Wind Tunnel

作　　者：易家宁 YI Jia-ning(AVIC Aerodynamics Research Institute,Shenyang 110034,China;Aeronautical Science and Technology Key Lab for High Speed High Reynolds Number Aerodynamic Research,Shenyang 110034,China)

机构地区：[1]中国航空工业空气动力研究院,辽宁沈阳110034 [2]高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《测控技术》2020年第7期93-97,共5页Measurement & Control Technology

摘　　要：相对于阶梯变速压颤振试验,连续变速压颤振试验具备更高的可靠性和效率,可以为先进飞行器的颤振边界预测及颤振特性分析提供更为安全可靠的技术支撑。为实现定马赫数连续变速压颤振试验技术,设计了连续变速压流场控制系统,通过引入解耦控制与专家PID控制优化了控制效果。风洞验证试验结果表明,该系统具有良好的控制效果,可满足定马赫数连续变速压流颤振试验对风洞流场控制指标的要求。Continuously increasing dynamic pressure flutter test is a safer,more efficient and more reliable technical support for flutter boundary prediction and flutter characteristics analysis of advanced aircraft.A control system for continuously increasing dynamic pressure flutter test is designed,of which the control effect is optimized by decoupling control and expert PID control.The results of wind tunnel tests show that the control system has good control effect,and can meet the flow field control requirement of continuously increasing dynamic pressure flutter test.

关 键 词：颤振试验 流场控制 连续变速压 解耦控制 专家PID控制 

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]