20073377July2007JournalofBeijingUniversityofAeronauticsandAstronauticsVo.l33No7馬鐵林馬東立張華(,100083):長航時無人機在飛行過程中受氣動載荷影響,其大展弦比機翼產生彎曲和扭轉變形,這種彈性變形嚴重影響飛機的飛行性能和飛行安全,不能將此種飛機機翼當作傳統的剛性機翼進行氣動分析.針對一真實復合材料大展弦比前掠機翼,采用氣動/結構一體化的分析方法,利用計算流體動力學(CFD)軟件FLUENT和計算結構動力學(CSD)軟件NASTRAN聯合求解,研究了在不同載荷情況下大展弦比柔性機翼靜氣動彈性變形對機翼氣動特性的影響.結果表明,大展弦比無人機機翼受載變形后升阻比降低,滾轉力矩和偏航力矩顯著增大,對飛機的縱向和橫側向氣動性能產生不利影響,同時也證明此CFD/CSD耦合計算方法可以應用到柔性機翼的氣動/結構一體化設計中.:CFD/CSD;大展弦比柔性機翼;靜氣動彈性;氣動特性;一體化設計:V221;V211.41:A:1001-5965(2007)07-0781-04Aerodynamiccharacteristicanalysisofhigh-aspectratioelasticwingMaTielinMaDongliZhangHua(SchoolofAeronauticScienceandEngineering,BeijingUniversityofAeronauticsandAstronautics,Beijing100083,China)Abstract:Theaerodynamicperformanceandflyingsafetyoflong-enduranceunmannedaerialvehicle(UAV)arelargelyaffectedbytheaeroelasticdistortionofitshigh-aspectratiowing.High-aspectratiowingofUAVisbendedandwtistedbytheairloadduringflightandcouldntbetreatedasatraditionalrigidwing.Theeffectofstaticaeroelasticdistortiontotheaerodynamiccharacteristicforarealhigh-aspectratiosweepforwardwingofcompositematerialunderdifferentloadstatuseswasanalyzed.Theintegrateddesignmethodcombinedaerodynamicwithstructuralwasadoptedinthisanalysisusingassociatedcomputationalfluiddynamics(CFD)programFLUENTandcomputationalstructualdynamics(CSD)programNASTRAN.Theresultshowsalif-tdragratiodropandaremarkableincreaseonrollingandyawingmomentswhichaffecttheportraitandlateralaerodynamicperformanceofUAVnegatively.TheresultalsoshowsthattheCFD/CSDcouplingcomputationalmethodologyisreliabletobeusedaerodynamic-structuralintegrateddesignofelasticwing.Keywords:CFD/CSD;high-aspectratioelasticwing;staticaeroelastics;aerodynamiccharacteristic;integrateddesign,,,,,..,,.2080,[1],.ARGON,90,MSC-:2006-06-28(1978-),:,,,matielin@yahoo.com.cn.7822007MSC.Flds.22,,.,,,,.[2].21,HI/NATRAN[3]CFL3D/GFEC[4]ZAERO/NATRAN[5]/,,,,,,,.,,,[6-7],,,.4~7[7].,.,,,,,/,,CFDFLUENTCDNAS-[7],TRAN,,,.,.,FLUENT,NATRAN2.1,1.2:FLUENT(,);1,;Nastran,;.,(1),~[8],,.,,.,,.,,,,.,.C=-ClBA#y?/2-sin+Cy?/21/2(1),LpLp,C;CALlB;C;#.,L;+1/2,,1/2..,,2/0b~6b0b~4b,,1g,3g.7:78312.331g516mm517.3mm,,,.31g3g.1g3g64,5.1g0.36b3,517mm,,1072mm,0.85b.37485962373g,,,30,,,,2m,,/3g,;,,,,;,,,.89,,KD,7~,7842007.4/,,:,,.10,.;,,C,lB,,.FLUENT/NASTRAN.CFD/CSD/11(References)[1]PalaciosR,CesnikC.Staticnonlinearaeroelasticityofflexibleslenderwingsincompressibleflow[R].AIAA-2005-1945,2005[2],.[J].,2004,22(4):85-88DengLidong,LiTian.Researchofnonlinearflightloadscalcu-lationonaflexibleaircraft[J].FlightDynamics,2004,22(4):85-88(inChinese)[3]PesonenU,AgarwalR.Artificialnetworkpredictionofaircraftaeroelasticbehavior[R].AIAA-2002-0947,2002[4]GumbertC,NewmanP,HouG.Effectofrandomgeometricun-certaintyonthecomputationaldesignofa3-Dflexiblewing[R].AIAA-2002-2806,200212,10,.m,,[5]PanzaJ,MakS.AeroservoelasticanalysisofaNASA-ALTAIRairvehicle[R].AIAA-2003-6500,20031112.,;CnlA=0b[6],,.CFD/CSD[J].,2006,27(1):33-37CC1.lBnBXuMin,AnXiaomin,ChenShilu.CFD/CSDcoupingnumer-icalcomputationalmethodology[J].ActaAeronauticaetAstro-nauticaSinica,2006,27(1):33-37(inChinese)1CCnBlB[7].--0.0009-0.0022-0.00350.00002-0.0001-0.00031g3g[D].:,,2005LiuJinhu.iMultidisciplinaryaerodynamic-structureoptimizationdesignoftheelasticwing[D].Xipan:NationalKeyLaboratoryofAerodynamicDesignandResearch,No