CAE技术在飞行器结构仿真中的应用-庄茁.

TSINGHUAUNIVERSITYCAE技术在飞行器结构仿真中的应用庄茁清华大学航天航空学院全国计算机辅助工程（CAE）技术与应用高级研讨会2005.08.22TSINGHUAUNIVERSITY人类需要借助各种工具来增强、延伸和扩大自己认识世界的能力，虚拟科学与工程(VirtualScienceandEngineering)正是用高科技手段构造出一种人工环境，帮助工程师和科学家创造一个时域和空域可变的虚拟世界，使人们能够在这个虚拟世界中纵观古今，瞬扶四海，实现从必然王国到自由王国的认识过程。CAE技术在飞行器结构仿真中的应用TSINGHUAUNIVERSITY清华大学航天航空学院成立于2004年5月18日清华大学航空学院的历史追溯到1930年TSINGHUAUNIVERSITYTSINGHUAUNIVERSITY清华大学航天航空学院教授35名（含两院院士5名），副教授40名；研究生380名，其中博士生200名，硕士生180名；本科生350名，其中国防定向生95名；宇航员工程硕士班XX名。学院概况工程力学系，航天航空系；宇航中心，航空技术中心，国防战略研究中心，空天信息研究中心。TSINGHUAUNIVERSITYTSINGHUAUNIVERSITYTSINGHUAUNIVERSITY宇航中心TSINGHUAUNIVERSITYCAE技术在飞行器结构仿真中的应用内容1.飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估2.飞行器结构的冲击失效与强度分析3.流体/结构耦合分析4.飞行器结构的强度和屈曲分析5.点阵格栅材料力学性能及其应用TSINGHUAUNIVERSITY1.飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估CAE技术在飞行器结构仿真中的应用TSINGHUAUNIVERSITYStructuralIntegrityofAircraftFailureofanEngineWidespreadFatigueDamageRepair飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYFRAMELAPJOINTSTRINGERSTRINGERSHELLPANELTEARSTRAPS飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估WFDTSINGHUAUNIVERSITYWidespreadFatigueDamage（WFD）•WFDIncreasesSafetyConcerns•MustbeabletoAssessWFDRisks•IncorporateProbabilisticMethodologies•IntegrateExistingProbabilisticandDeterministicProcedurestoPerformWFDAnalyses•PerformStudiesonSelectedAgingAircraftComponentstoDemonstrateFeasibility•Providea‘Complete’Stand-AloneAnalysisCapabilityfortheAircraftIndustry飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYDeterministicAnalysisRequirements•Fast,AccurateCalculationofStressIntensityFactor–Elastic-PlasticFiniteElementAlternatingMethod(EPFEAM)•MustAcceptaWideVarietyofInputsfromProbabilisticRoutine–Loads,Properties,Geometry,Cracks飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估WFDApplications•Boeing737LapSpliceJoint•707WingSkin•PressureDomeTSINGHUAUNIVERSITYWidespreadFatigueDamageFRAMELAPJOINTSTRINGERSTRINGERSHELLPANELTEARSTRAPS飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYFuselageFractureAnalysisApproachCaptureGlobalLoadFlowDetailedModelsofStingersandFramesFractureAnalysisGlobalModelIntermediateModelLocalModelThreeLevelsofAnalysisStandardFEPackageFiniteElementAlternatingMethod飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYSystemArchitectureStandardFEMAnalysisPWFDInputGlobalModelIntermediateModelLocalModelStandardFEMAnalysisEPFEAMFractureSolutions飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYSKIN:8-NODESHELLFRAME:3-NODEBEAMSTRINGER:3-NODEBEAMRIVET:SPRINGANALYSISAPPROACH:STANDARDFEMGlobalModel飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYSKIN:8-NODESHELLFRAME:4-NODESHELLSTRINGER:4-NODESHELLRIVET:SPRING/BEAMIntermediateModel飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYLocalModelSKIN:8-NODEISOPARAMETRICELEMENT飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYIsolatedSkinwithReactionForcesfromtheStiffenersFarFieldTractionFastenerReactionForcesTSINGHUAUNIVERSITYAutomationofAnalysis•MeshGeneration–AutomaticallyfromPhysicalInputssuchasSkinThickness,StringerSpacingetc.•HierarchicalAnalysis–Global-Intermediate-LocalBenefit:EliminatesAnalysisDifficultiesforUsers飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYWFDConfiguration1:Boeing737LapJoint飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYIntermediateModel737Frame飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYGlobalAnalysisResultsDisplacements飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYGlobalAnalysisResultsMagnifiedDisplacements飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYGlobalAnalysisResultsStresses&Displacements飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYGlobalAnalysisResultsStresses飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYIntermediateAnalysisResults:HoopStresses飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITY飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估IntermediateAnalysisResults:HoopStressesTSINGHUAUNIVERSITYFiniteElementAlternatingMethodAdvantages•FastandAccurate•NoExplicitModelingofCrackTip•SameMeshcanbeUsedforDifferentCrackConfigurations•ElasticandElasticPlastic•2Dand3D飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYAdvanced2DFEAM•ElasticorElastic-PlasticAnalyses•PlasticityTheory:FloworDeformationTheory•ComputationofK,JandT*•StableTearing•MixedModeFracture•MultipleCracks:ArbitraryLocationandOrientation•Loading:Traction,Nodalforce,Non-zeroDisplacement,ResidualStresses•ResidualStrengthCalculations•ExpandedElementLibrary飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITYAdvanced3DFEAM•ElasticorElastic-PlasticAnalyses•PlasticityTheory:DeformationTheoryOnly•ComputationofK,JandT*•MixedModeFracture•MultipleCracks:ArbitraryLocationandOrientation•Loading:Traction,Nodalforce,Non-zeroDisplacement,ResidualStresses•ResidualStrengthCalculations•ExpandedElementLibrary飞行器结构疲劳损伤蔓延的断裂力学计算和风险评估TSINGHUAUNIVERSITY2飞行器结构的冲击失效与强度分析CAE技术在飞行器结构仿真中的应用TSINGHUAUNIVERSITY•14,670shellelements•Rotatingvelocity:10,000rpm•DiameterofCasing:900mmFanBladesCasingFanRotorModel飞行器结构的冲击失效与强度分析飞鸟撞击发动机叶片TSINGHUAUNIVERSITY飞行器结构的冲击失效与强度分析•ObtainsteadystaterotationsolutionwithABAQUS/Standardandpasssteadystatedeformedshape,stressesandstrainsintoABAQUS/Explicitforsubsequentanalysis•BirdstrikeBirdweightImpactvelocityCase1680g120m/sCase2680g200m/sCase31814g200m/sTSINGHUAUNIVERSITY飞行器结构的冲击失效与强度分析BirdCylindricalshapeNearlyincompressiblematerialShearfailureCasingDefinedasrigidbodyBladesElastic-plasticmaterialContactBetweenbladesan