非线性叶间黏弹减摆器对直升机

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1、科技论坛:www.tech-domain.com维普资讯科技论坛http://www.cqvip.com第28卷第3期航空学报VOI．28NO．32007正5月ACTAAERONAUTICAETASTR()NAUTICASINICAMav2O07文章编号：10006893(2007)03055006非线性叶间黏弹减摆器对直升机空中共振的影响分析王波，李书，张晓谷(北京航空航天大学飞机设计所，北京100083)InfluenceAnalysisofHelicopterAirResonancewithNonlinearInterbladeVisco

2、elasticDampersWANGBo，I．IShu，ZHANGXiao—gu(InstituteofAircraftDesign，BeijingUniversityofAeronauticsandAstronautics，Beijing100083，China)摘要：建立带非线性叶问黏弹减摆器的直升机旋翼／机体耦合动稳定性分析模型。与全机飞行力学平衡计算相结合，旋翼／机体耦合动稳定性分析模型考虑前飞状念桨叶变距操纵、机体姿态角和桨毂纵向安装角。针对具有非线性特性的叶间黏弹减摆器，采用基于复模量的非线性VKS改进模型、Simulink时域仿真

3、和多桨叶坐标变换等效阻尼识别法分析直升机悬停、前飞状态下旋翼机体耦合动稳定性及减摆器双频动幅值，并就减摆器布局、全机总重以及前飞速度对桨叶摆振后退型模态阻尼的影响进行分析。结果表明：南悬停到前飞直升机动稳定性一般均下降．一定速度后又上升；加卜减摆器能消除前飞不稳定区；叶间黏弹减摆器抬头连接能提高模态阻尼。关键词：直升机动力学；空中共振；叶问黏弹减摆器；非线性特性；参数分析中图分类号：V212．5；V214．42文献标识码：AAbstract：Ananalyticalmodelisdevelopedforhelicopterrotor／fusel

4、agecoupleddynamicstabilitYwithinterbladenonlinearviscoelasticdampers．Coupledwiththecalculationofhelicopterequilibriumintheflightdy—namics，theanalyticalmodelconsidersthefactorsasbladetorsionmanipulation，fuselageposeangleandhublongitudinalinstallangle．Alongwiththebladeviscoela

5、sticdampernonlinearproperties，animprovednonlinearVKSmodelbasedoncomplexmodulus，Simulinkemulationintime—domainandequivalentdampingidentifica—tionbasedOnnumericalmulti—bladecoordinatetransformationareappliedinpredictionsofrotor／fuselagecou—pieddynamicstabilitiesinhoverandforwa

6、rdflight，andthedamperdynamicamplitudeintheconditionofdualfrequency．Effectsofthedamperconfigurations，grossweightandflightvelocityontheregressivelagmodaldampingarestudied．Therewww.tech-domain.comsultsdemonstratethatthehelicopterdynamicsstabilitiesdeclineinthestartingtimetOforw

7、ardfly，butascendafterspecificvelocity，andthattheairresonancecouldbeavoidedwithinterbladeviscoelasticdampersaddedandtheregressivelagmodaldampingcouldbeincreasedbylead—upjointofthedamper．Keywords：helicopterdynamics；airresonance；interbladeviscoelasticdamper；nonlinearcharacteris

8、tic；para—metricanalysisEC155的飞行试验口表明，黏弹减摆器采用直升机定常前飞时，桨叶处于非对称流场，增叶间连接，通过调整连接