简介：冠的stents是通过导管送到堵住的容器的金属卷或网孔试管，它被汽球扩展再开并且支架目标容器。最近，特殊的药被stents(drug-elutingstents)带进一步在stenting过程以后减少in-stent狭窄率。然而，stents的biomechanical特征上的不断的学习为在stents和织物之间的更好的相互作用是必要的，或提供为drug-elutingstents装载站台的更合适的药。这份报纸的目的是显示出有限元素方法怎么能被用来学习弄弯的冠的stents的房间区域和神气分发变化。一样的弯曲变丑被用于冠的stent由一个僵硬弄弯的容器建模的二个广告。结果证明stent设计在把状况弄弯下面影响了房间区域和神气分发的变化。有连接的stent与山峰山峰在外部弯曲，和stent有更多的房间区域变化()神气设计能有神气接触并且在内部弯曲重叠。在结论，这个有限元素方法能被用来学习并且比较弄弯的stents的房间区域和神气分发变化，并且在新stents的严峻、改进的biomechanical特征为设计者提供一个方便工具。

简介：Anewlydesignedstrutisproposedinthispaperforfuelinjectionandflameholdinginaliquid-kerosene-fueledsupersoniccombustor.Thethicknessofthestrutis8mmandthefrontblockageisabout8%.Thecharacteristicofthisstrutisthatextraoxygencanbeinjectedthroughasetoforificesatthebackofthestrut,whichcanchangethelocalflowfieldstructureandER(EquivalenceRatio).Basedontheabovementionedstrut,astablelocalflameisgeneratedatthebackofthestrutandthemaincombustioncanbeorganizedaroundthislocalfire.Numericalsimulationisconductedtocomparethelocalflowfielddistributionatthebackofthestrutwith/withoutextraoxygeninjection.Experimentsareconductedtotestthecombustioncharacteristicsbasedonthisfuelinjectionandflameholdingstrategy.Thetemperaturedistributionwhichcanreflectthelocalflamecharacteristichasbeenmeasuredintheexperimentsconductedundercoldincomingsupersonicairflowcondition.Inaddition,theoverallcombustionperformanceinafull-scalesupersoniccombustorhasbeenevaluatedintheexperimentsconductedunderhotincomingsupersonicairflowcondition.Resultsshowthatthisstrutstrategyisverypromisingsinceitcanorganizestablesupersoniccombustionatthecenterofthecombustorwithoutanycavityorrearwardfacingstep.Besidesthat,evenwiththe8mmthickstrut,thecombustioncanbestableinawiderangeofERfrom0.25-1byusingliquidroom-temperaturekerosene.

简介：Thispaperisconcernedwiththedynamicsofaspacecraftwithmulti-strutpassivedamperforlargeflexibleappendage.Thedamperplatformisconnectedtothespacecraftbyaspherichinge,multipledampingstrutsandarigidstrut.Thedampingstrutsprovidedampingforceswhiletherigidstrutproducesamotionconstraintofthemultibodysystem.TheexactnonlineardynamicalequationsinreducedorderformarefirstlyderivedbyusingKane＇sequationinmatrixform.Basedontheassumptionsofsmallvelocityandsmalldisplacement,thenonlinearequationsarereducedtoasetoflinearsecond-orderdifferentialequationsintermsofindependentgeneralizeddisplacementswithconstantstiffnessmatrixanddampingmatrixrelatedtothedampingstrutparameters.Numericalsimulationresultsdemonstratethedampingeffectivenessofthedamperforboththemotionofthespacecraftandthevibrationoftheflexibleappendage,andverifytheaccuracyofthelinearequationsagainsttheexactnonlinearones.

简介：Inordertoshortenaero-engineaxiallength,substitutingthetraditionallongchordthickstrutdesignaccompaniedwiththetraditionallowpressure(LP)stagenozzle,LPturbineisintegratedwithintermediateturbineduct(ITD).Inthecurrentpaper,fivevanesofthefirststageLPturbinenozzleisreplacedwithloadedstrutsforsupportingtheengineshaft,andprovidingoilpipescircumferentiallywhichfulfilledtheareo-enginestructurerequirement.However,theirbulkygeometricsizerepresentsamoreeffectiveobstacletoflowfromhighpressure(HP)turbinerotor.ThesefivestrutsgiveobviousinfluencefornotonlytheLPturbinenozzlebutalsotheflowfieldwithintheITD,andhencecausehigherloss.NumericalinvestigationhasbeenundertakentoobservetheinfluenceoftheNozzle-StrutintegrateddesignconceptontheflowfieldwithintheITDandthenearbynozzleblades.Accordingtothecomputationalresults,threemainconclusionsarefinallyobtained.Firstly,anoticeablelowspeedareaisformednearthestrut'sleadingedge,whichisnodoubtcausedbythepotentialfloweffects.Secondly,moresevereradialmigrationofboundarylayerflowadjacenttothestrut'spressuresidehavebeenfoundnearthenozzle'strailingedge.Suchboundarylayermigrationisobvious,especiallyclosetotheshrouddomain.Meanwhile,radialpressuregradientaggravatesthisphenomenon.Thirdly,velocitydistributionalongthestrut'spressuresideonnozzle'ssuctionsurfacediffers,whichmeansloadingvariationofthenozzle.Anditwillnodoubtcausenonuniformflowfieldfacedbythedownstreamrotorblade.