超声速风洞带舵机状态全尺寸舵颤振亚临界试验  

Supersonic Wind Tunnel Subcritical Flutter Test Research on a Full Scale Rudder Installed in Steering Gear

作　　者：王珏 王誉超 季辰[1] WANG Jue;WANG Yuchao;JI Chen(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空天防御》2023年第2期77-83,共7页Air & Space Defense

基　　金：国家自然科学基金资助项目(11702285)。

摘　　要：为研究带舵机状态的全尺寸舵超声速颤振特性,设计了基于FD-12暂冲式亚跨超三声速风洞的舵面气动弹性试验平台,并采用亚临界颤振试验方法,开展全尺寸舵面安装在真实舵机舱状态下的实物颤振特性研究。试验中,马赫数Ma=1.5,采用固定马赫数连续变动压的风洞开车方式,应用3种亚临界颤振边界预测方法计算颤振边界。对加速度传感器测量得到的舵面振动响应数据进行颤振边界预测。结果表明:采用Houbolt-Rainey、Peak-Hold、Zim-erman-Weissenburger方法预测得到的颤振动压分别为0.070、0.072、0.073 MPa,三者基本一致。To study the supersonic flutter characteristics of the full-scale rudder-installed steering gear,a rudder model aeroelasticity test platform based on the FD-12 wind tunnel was designed by the China Academy of Aerospace Aerodynamics.The subcritical flutter test method was used to study the characteristics of the full-scale rudder installed in an actual steering gear.The rudder model was tested in a wind tunnel with a fixed Mach number of 1.5 and continuously raising the dynamic pressure.The flutter boundary was captured by three subcritical flutter boundary prediction methods:the Houbolt-Rainey method,the Peak-Hold method and the Zimmerman-Weissenburger method.The flutter boundaries were predicted using the rudder vibration response data measured by the accelerometers.The flutter dynamic pressure predicted by three subcritical flutter boundary prediction methods were respectively 0.070,0.072 and 0.073 MPa,which were almost the same.

关 键 词：超声速 颤振试验 亚临界颤振边界预测 气动弹性 风洞试验 

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]