微型舵机的结构动力学分析
Abstract
Theactuatormainlycontrolstheattitudeofthemissileduringflight,suchasrolling,
pitching,andyawing.Currently,commonlyusedactuatorsystemsmainlyincludehydraulic,
pneumatic,andelectricactuatorsystems.Comparedtotheothertwotypes,theelectric
actuatorsystemhasadvantagessuchasstrongadaptability,smallsize,andhighreliability.To
meettherequirementofminiaturizationofthemicroactuator,themicroelectricactuatoris
takenastheresearchobject,andthestructureofthemicroactuatorisdesigned.Thedynamic
characteristicsandstructuraldynamicsofthemicroactuatorareanalyzed.Themainresearch
contentsareasfollows:
(1)Designetheoverallstructuralschemeofthemicroactuator.Themicroactuator
consistsoffourindependentlymovingactuatortransmissionmechanismsthatforma
cross-shapedaerodynamiclayoutfortheoverallstructureofthemicroactuator.Each
independentlymovingactuatortransmissionmechanismincludesaDCmotor,areduction
transmissiondevice,anactuatorsurface,andanangledetector.Tomeetthedesign
requirementsforminiaturization,thereductiontransmissiondeviceadoptsatwo-stage
transmissionthatcombinesgearpairsandscrew-nutpairs.
(2)Utilizevirtualprototypingtechnologytoconductsimulationanalysisofthe
independentlymovingactuatortransmissionmechanism.Thesimulationresultsshowthatthe
actuatorsurfacedeflectionangleandangularvelocitybothmeetthetechnicalspecifications.
UseANSYSsoftwaretoperformstructuraldynamicsanalysisofthemicroactuator,obtaining
modalanalysisandresponsespectrumanalysisresultsofthe