简介：Itisanimportantcontrolprocesstooperatemotionofansubmergencerescuevehicle(SRV).Seeingthatthemotionofthesubmergencerescuevehicleisspecial,itisnecessarytoemploynon-linearpredictivecontrolsystem.Forthisreason,continuousdynamicperformanceofthesystem,thelogicalcomponentsandtheoperativerestraintsareexpressedasthenon-linearequationsofstatewiththeinequalityrestraints,andthemodelprincipleofhybridsystemisintroduced.TheconclusionshowsthatitcomestruetoexactlycontrolpositionandattitudeoftheSRVbymeansofnon-linearmodelpredictivecontrol.Thetestinamodelbasinhasalsoprovedthattheabovemethodsareefficient.

简介：Therandomstepmaneuverwithuniformlydistributedstartingtimeshasthedisadvantagethatitcannotfocusthestartingtimeonthemoreefficiencytime.Itdecreasesthepenetrationprobability.Toresolvethisproblem,arandomsteppenetrationalgorithmwithnormaldistributionstartingtimeisproposed.Usingtheshapingfiltersandadjointsystemmethod,themissdistancewithdifferentstartingtimescanbeacquired.Accordingtothepenetrationstandard,thetimewindowensuringsuccessfulpenetrationcanbecalculatedanditisusedasthe3σboundofthenormallydistributedrandommaneuver.Simulationresultsindicatethatthenormallydistributedrandommaneuverhashigherpenetrationprobabilitythantheuniformlydistributedrandommaneuver.

简介：Inremotesensingorlasercommunicationspacemissions,spacecraftneedfastmaneuverandfaststabilizationinordertoaccomplishagileimagingandattitudetrackingtasks.However,fastattitudemaneuverscaneasilycauseelasticdeformationsandvibrationsinflexibleappendagesofthespacecraft.Thispaperfocusesonthisproblemanddealswiththecombinedcontroloffastattitudemaneuverandstabilizationforlargecomplexspacecraft.Themathematicalmodelofcomplexspacecraftwithflexibleappendagesandmomentumbiasactuatorsonboardispresented.Basedontheplantmodelandcombinedwiththefeedbackcontroller,modalparametersoftheclosed-loopsystemarecalculated,andamultiplemodeinputshaperutilizingthemodalinformationisdesignedtosuppressvibrations.Aimingatreducingvibrationsexcitedbyattitudemaneuver,aquinticpolynomialformrotationpathplanningisproposedwithconstraintsontheactuatorsandtheangularvelocitytakenintoaccount.Attitudemaneuversimulationresultsofthecontrolsystemswithinputshaperorpathplanninginloopareseparatelyanalyzed,andbasedontheanalysis,acombinedcontrolstrategyispresentedwithbothpathplanningandinputshaperinloop.Simulationresultsshowthatthecombinedcontrolstrategysatisfiesthecomplexspacecraft’srequirementoffastmaneuverandstabilizationwiththeactuators’torquelimitationsatisfiedatthesametime.

简介：有由动量车轮的一根伸臂横梁被学习的一个附器的充满液体的太空船的态度演习。动态方程被尖动量和力量平衡原则的保存导出。动量车轮的反馈控制策略被申请态度演习。在演习过程的太空船的剩余点头随着一些选择参数变化，例如稳定的州的时间，液体容器的地点和附器，并且附器参数。结果显示在修理身体的坐标系统的第二和第四个象限和主要身体的墙的第二个象限的地点是为如果他们能随机被放，把液体集装箱和附器放比另外的地点的更好的选择。更高的密度和更厚的生气的节对如果他们能被改变，降低剩余点头更好。轻附器能作为僵硬身体被建模，它不过比一个灵活模型导致一个更大的剩余点头。剩余点头与增加起始的sloshing的绝对值减少尖高度。

简介：Objective:Toinvestigatetheefficacyofquickrepositioningmaneuverforhorizontalsemicircularcanalbenignparoxysmalpositionalvertigo(H-BPPV).Methods:Clinicaldataof67patientswithH-BPPVwhounderwentquickrepositioningmaneuverinourhospitalfromJuly2009toNovember2014wereretrospectivelyanalyzed.Themaneuverinvolvedrotatingthepatientintheaxialplanefor180fromtheinvolvedsidetowardscontralateralsideasquicklyaspossible.Results:Completesymptomresolutionwasachievedin61patients(91.0%)atoneweekandin64patients(95.5%)at3monthspost-treatment.Duringtherepositioningmaneuverprocess,therewerenoobviousuntowardresponsesexcepttransientnauseawithorwithoutvomitinginafewpatients.Conclusion:TheresultsindicatethatthequickrepositioningmaneuverisaneasyandeffectivealternativetreatmentinthemanagementofHBPPV.

简介：Thepresentpaperinvestigatesthechaoticattitudedynamicsandreorientationmaneuverforcompletelyvis-cousliquid-filledspacecraftwithflexibleappendage.AlloftheequationsofmotionarederivedbyusingLagrangianmechanicsandthentransformedintoaformconsistingofanunperturbedpartplusperturbedtermssothatthesystem'snonlinearcharacteristicscanbeexploitedinphasespace.Emphasesarelaidonthechaoticattitudedynamicsproducedfromcertainsetsofphysicalparametervaluesofthespace-craftwhenenergydissipationactstoderivethebodyfromminortomajoraxisspin.Numericalsolutionsoftheseequa-tionsshowthattheattitudedynamicsofliquid-filledflexiblespacecraftpossessescharacteristicscommontorandom,non-periodicsolutionsandchaos,anditisdemonstratedthatthedesiredreorientationmaneuverisguaranteedbyusingapairofthrusterimpulses.Thecontrolstrategyforreorientationmaneuverisdesignedandthenumericalsimulationresultsarepresentedforboththeuncontrolledandcontrolledspinstransition.

简介：Toreachahigherlevelofautonomyforunmannedcombataerialvehicle(UCAV)inaircombatgames,thispaperbuildsanautonomousmaneuverdecisionsystem.Inthissystem,theaircombatgameisregardedasaMarkovprocess,sothattheaircombatsituationcanbeeffectivelycalculatedviaBayesianinferencetheory.Accordingtothesituationassessmentresult,adaptivelyadjuststheweightsofmaneuverdecisionfactors,whichmakestheobjectivefunctionmorereasonableandensuresthesuperioritysituationforUCAV.Astheaircombatgameischaracterizedbyhighlydynamicandasignificantamountofuncertainty,toenhancetherobustnessandeffectivenessofmaneuverdecisionresults,fuzzylogicisusedtobuildthefunctionsoffourmaneuverdecisionfactors.Accuracypredictionofopponentaircraftisalsoessentialtoensuremakingagooddecision;therefore,apredictionmodelofopponentaircraftisdesignedbasedontheelementarymaneuvermethod.Finally,themovinghorizonoptimizationstrategyisusedtoeffectivelymodelthewholeaircombatmaneuverdecisionprocess.Varioussimulationsareperformedontypicalscenariotestandclose-indogfight,theresultssufficientlydemonstratethesuperiorityofthedesignedmaneuverdecisionmethod.

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简介：Whenanaircraftishoveringordoingadive-hikeflightatafixedspeed,aconstantadditionalinertialforcewillbeinducedtotherotorsystemoftheaero-engine,whichcanbecalledaconstantmaneuverload.Takehoveringasanexample.AJeffcottrotorsystemwithabiasedrotorandseveralnonlinearelasticsupportsismodeled,andthevibrationcharacteristicsoftherotorsystemunderaconstantmaneuverloadareanalyticallystudied.Byusingthemultiple-scalemethod,thedifferentialequationsofthesystemaresolved,andthebifurcationequationsareobtained.Then,thebifurcationsofthesystemareanalyzedbyusingthesingularitytheoryforthetwovariables.IntheEG-plane,whereEreferstotheeccentricityoftherotorandGrepresentstheconstantmaneuverload,twohysteresispointsetsandonedoublelimitpointsetareobtained.Thebifurcationdiagramsarealsoplotted.Itisindicatedthattheresonanceregionsofthetwovariableswillshifttotherightwhentheaircraftismaneuvering.Furthermore,themovementalongthehorizontaldirectionisfasterthanthatalongtheverticaldirection.Thus,thedifferentoverlappingmodesofthetworesonanceregionswillbringaboutdifferentbifurcationmodesduetothenonlinearcouplingeffects.Thisresultlaysatheoreticalfoundationforcontrollingthestabilityoftheaero-engine’srotorsystemunderamaneuverload.

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