第6卷第2期2023年6月空天防御AIR&SPACEDEFENSEVol.6，No.2Jun.，2023超声速风洞带舵机状态全尺寸舵颤振亚临界试验王珏，王誉超，季辰（中国航天空气动力技术研究院，北京100074）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-er⁃man-Weissenburger方法预测得到的颤振动压分别为0.070、0.072、0.073MPa，三者基本一致。关键词：超声速；颤振试验；亚临界颤振边界预测；气动弹性；风洞试验中图分类号：V211.74文献标志码：A文章编号：2096-4641（2023）02-0077-07SupersonicWindTunnelSubcriticalFlutterTestResearchonaFullScaleRudderInstalledinSteeringGearWANGJue，WANGYuchao，JIChen（ChinaAcademyofAerospaceAerodynamics，Beijing100074，China）Abstract:Tostudythesupersonicfluttercharacteristicsofthefull-scalerudder-installedsteeringgear,aruddermodelaeroelasticitytestplatformbasedontheFD-12windtunnelwasdesignedbytheChinaAcademyofAerospaceAerodynamics.Thesubcriticalfluttertestmethodwasusedtostudythecharacteristicsofthefull-scalerudderinstalledinanactualsteeringgear.TheruddermodelwastestedinawindtunnelwithafixedMachnumberof1.5andcontinuouslyraisingthedynamicpressure.Theflutterboundarywascapturedbythreesubcriticalflutterboundarypredictionmethods:theHoubolt-Raineymethod,thePeak-HoldmethodandtheZimmerman-Weissenburgermethod.Theflutterboundarieswerepredictedusingtheruddervibrationresponsedatameasuredbytheaccelerometers.Theflutterdynamicpressurepredictedbythreesubcriticalflutterboundarypredictionmethodswererespectively0.070,0.072and0.073MPa,whichwerealmostthesame.Keywords:supersonic；fluttertest；subcriticalflutterboundaryprediction；aeroelasticity；windtunneltest0引言战斗机、导弹等高速飞行器全动舵的颤振是其气动弹性设计中需要关注的重要问题之一。采用缩比模型开展风洞...
