次 言 范圍 文件（REFERENCE 的符合性驗證計劃（CROSS-REFERENCEDCERTIFICATION 術(shù)語和定義（TERMSand 油箱結(jié)構(gòu)(Fuel 系統(tǒng)組成和原理(SystemComposingand 翼油箱結(jié)構(gòu)(Center 翼油箱結(jié)構(gòu)介紹(Introductionof 惰化系統(tǒng)(Inerting 系統(tǒng)組成和原理(SystemComposingand 系統(tǒng)功能（System 系統(tǒng)接口(System 燃油系統(tǒng)(Fuel 系統(tǒng)組成和原理(SystemComposingand 系統(tǒng)功能(System 動力裝置 系統(tǒng)組成和原理(SystemComposingand 系統(tǒng)功能(System 電氣線路互聯(lián)系統(tǒng) 系統(tǒng)組成和原理(SystemComposingand 飛控作動系統(tǒng)(TheFightControlActuation 系統(tǒng)組成和原理(SystemComposingand 空調(diào)系統(tǒng)(Air-conditioning 系統(tǒng)架構(gòu)和組成(SystemArchitectureand 系統(tǒng)原理及安裝位置(SystemPrincipleand 氣源系統(tǒng)和機翼防冰系統(tǒng) aticSystemandWinganti-ice 系統(tǒng)功能及原理(SystemFunctionand 安裝位置(System 防火系統(tǒng)(Fireprotection 組成 功能 原理 引氣泄漏過熱探測(Bleedairleakageoverheat 系統(tǒng)安全性要求(SYSTEMSAFETY 源自功能評估的安全性要求(SafetyRequirementsFrom 源自初步系統(tǒng)安全性評估的安全性要求(SafetyRequirementsFrom 構(gòu)型管理(Configuration 構(gòu)型管理的目標(ConfigurationManagement 惰化系統(tǒng)構(gòu)型項(Configuration 符合性驗證思路 符合性方法（COMPLIANCE 供應(yīng)商驗證工作（R 供應(yīng)商概述(r 供應(yīng)商支持計劃(rCertificationSupport TSO/VDA取證計劃(TSO/VDA 符合性驗證試驗（CERTIFICATION 符合性文件（CERTIFICATIONDELIVERABLES 言C919飛機系統(tǒng)/專業(yè)級符合性驗證計劃（CP）C919飛機型號合格證申請方（中國商并與方（中國民用航空局及其機構(gòu)，以下簡稱CAAC）討論協(xié)商一致，COMAC和CAAC通過其代表的批準，表示雙方都將認可并遵守本CP的內(nèi)容。合性驗證工作實施之前足夠長的時間通知CAAC確切時間，以保障有足夠的時間進行。Thepresent isthecertificationplanofexplosionpreventionofC919Airplane.Explosionpreventioncertificationplan(CP)ofC919Airplaneisthe stodescribethecertificationtasksfortheC919Airplanetypeapplicant(CommercialAircraftCorporationOfChina,,COMAC).ThisCPisproposedbyCOMAC,discussedandagreedbytheauthority(CivilAviationAgencyofChina,oritsdelegateorganization,CAAC).COMACandCAACrepresentatives’approvaldemonstratesthatbothsidesacknowledgeandwillexecutethisCP.Thepresent describesthelogicrelationshipofthecertificationactivities.COMACpromises:theimplementationplanwillbedescribedinthe<ExplosionpreventionCertificationSchedule>.COMACwillinformCAACtheexacttimeofeachcertificationactivitybeforeexecutionthroughtheacceptedprocedurebetweenbothsidestoensurethatCAAChavesufficienttimetoreview.范圍ThisspecifiesC919AircraftfuelexplosionpreventioncertificationThisisapplicabletotheC919Airplane2文件（REFERENCE本文件。凡是不注版本的文件，其版本（包括所有的修改單）適用于本文件。Thefollowingreferenced sareindispensablefortheapplicationofthis .Forreferenceswithedition,onlytheeditioncitedapplies.Forreferenceswithoutedition,thelatesteditionofthereferenced (includinganyamendments)applies.CCAR- 類飛機適航標 C919飛機符合性方法表 C919飛機通用技術(shù)規(guī)范 C919飛機惰化系統(tǒng)設(shè)計方案 飛機惰化系統(tǒng)初步功能性評 FUELIGNITIONSOURCEPREVENTIONGUIDLINES FUELFLAMMABILITYREDUCTIONMEANS3的符合性驗證計劃（CROSS-REFERENCEDCERTIFICATIONThereferencedcertificationplansofthepresentarelistedinTable表 的符合性驗證計Table ReferencedCertification CPFileMainflycontrolsystemcertification controlsystemto CPFilerequirementofVerficationEWISsystemtosatisfyrequirementigination，Air-conditioningsystem&airsourcesystemcertificationplanAir-conditioningsystem&airsourcesystemtosatisfyrequirementofiginationVerficationfueltosatisfyrequirementofiginationresource VerficationPowerplantsystemtosatisfyrequirementofFireprotectionspecialtycertification protectionsystemtosatisfyrequirementofiginationStructurespecialtycertificationVerficationStructureto igination術(shù)語和定義（TERMSand機隊平均可 救能力（即獨立的從受限空間中逃離）、受傷或急癥風險的空氣環(huán)境。ThetermsanddefinationsareusedinthisFleetaverageflammabilityexposureisthepercentageoftheflammabilityexposureevaluationtime(FEET)eachfuelullageisflammableforafleetofanairplanetypeoperatingovertherangeofflightlengthsinaworld-widerangeofenvironmentalconditionsandfuelproperties.FlammabilityExposureEvaluationTime(FEET).Thetimefromthestartofpreparingtheairplaneforflight,throughtheflightandlanding,untilallpayloadisunloaded,andallpassengersandcrewhavedisembarked.IntheMonteCarloprogram,theflighttimeisrandomlyselectedfromtheFlightLengthDistribution.Thepre-flighttimesareprovidedasafunctionoftheflighttime,andthepost-flighttimeisaconstant30Hazardousatmosphere.Anatmospherethatmayexposemaintenance nel,passengersorflightcrewtotheriskofdeath,incapacitation,impairmentofabilitytoself-rescue(thatis,escapeunaidedfromaconfinedspace),injury,oracuteillness.MonteCarloysis.Theyticalmethodthatisspecifiedinthisappendixasthecompliancemeansforassessingthefleetaverageflammabilityexposuretimeforafuel.Oxygenevolutionoccurswhenoxygendissolvedinthefuelisreleasedintotheullageasthepressureandtemperatureinthefuelarereduced.Inerting.Aprocesswhere bustiblegasisintroducedintotheullageofafuelsothe esnon-系統(tǒng)描述（SYSTEM油箱結(jié)構(gòu)(Fuel系統(tǒng)組成和原理(SystemComposingandThewingstructerofC919aircraftconsistsofmainwingsurfaceandcontrolsurface.Themainwingsurfaceiscomposedofcenterwing,outerwingandwinglet.Thecontrolsurfaceconsistsofailerons,trailing-edgeflaps,leading-edgeflapsandspoilers.Atthesideoffuselage,1#ribisdesignedtobeaproductionbreakdowninterfacewheretheouterwingandcenterwingbuttjoint.The27#ribisdesignedtobeainitialbreakdowninterfacewhereouterwingandwingletbuttjoint.TheC919aircraftadoptthree layout,onecenterwing andtwoouterwing.The6#ribisafuelinterfaceribbetweenthecenterwingfuel andtheouterwingfuel.The22#ribistheouterwing endrib.The isarrangedbetween22#riband25#翼油箱結(jié)構(gòu)(Center翼油箱結(jié)構(gòu)介紹(Introductionof 43框連接，弦向長度為2790.2mmCWBislocatedinthemid-fuselageinbetweentheframe37,43andRib1.Theupperandlowerpanelareconnectedwithfloorbeamandkeelbeamrespectively,asshowninthefigurebelow.CWBisconfiguratedbyfrontspar,rearspar,frontintermediatespar,rearintermediatespar,upper/lowerpanel,left/rightrib.2翼油箱結(jié)構(gòu)組件(CompositeofCenterCWBupperpanelspanwiselengthis3823mmandcoursedirectionlengthis2773mm.Manufacturedbyco-bondedautolayupskinand17handlayupstringers.CWBlowerpanelspanwiselengthis3823mmandcoursedirectionlengthis2790mm.Manufacturedbyco-bondedautolayupskinand15handlayupstringers.CWBfrontsparspanwiselengthis3837mmandheightis620mm.Configuratedbyspar(includingweb,upperflangeandlowerflangeconnectingwithfloorbeamandpressuredeckrespectively),upperflange,stiffener,transversereinforcementandfittings.Handlayupprocessingisappliedforallthecompositecomponents.Secondarybondingisappliedforstiffenerandwebassembling.CWBspanwiselengthis3833mmandheightis770mm.Configuratedbyspar,stiffenernon-loadingmouthpiece.Openingontherearsparisforassemblyandrepair,whichisreinforcedbytitaniumpanel.Handlayupprocessingisappliedforallthecompositecomponents.Secondarybondingisappliedforstiffenerandwebassembly.桁通過高鎖螺栓機械連接。兩端與左右1號肋通過鋁合金型材連接。展向梁在展向梁上各布置Intermediatesparsarecompositestiffenedpanels,includingwebandstiffener.Thefittings,flangeandjointsaremadefromaluminum.Handlayupprocessingisappliedforallthecompositecomponentsandco-bondedtogether.Intermediatesparsareconnectedwithupper/lowerpanelbyhi-lockpin,andconnectedwithleft/rightrib1byaluminumjointplates.Openingisdesignedoneachspartoprovideaccessforcheckingandrepair.Nomouthpieceontheopeningforfreefuelpass.1號肋航向尺寸為2757mm，前梁處高度為670mm，后梁處高度為828mm1065mm。1號肋由上、下緣條，前、后三叉接頭、下連接帶板和腹板組合而成。上、下緣條，前、后三叉接頭、下連接帶板材料為鈦合金，1號肋腹板為鋁合金。Coursedirectionlengthis2757mm，withvariousheight-670mminfront，828mmonthebackand1065mmin um.Rib1isconformedbyweb,upper/lowerflange,front/rearcrossjointplatesandlowerjointplate.Exceptaluminumweb,theotherpartsareallmadebytitanium. 外翼主翼面(OuterTheoutermainwingsurfaceconsistsofouterwingboxandwingleading&trailing外翼盒段(OuterWingTheouterwingboxisaall-metaldouble-spartraditionalstructure;itconsistsoffront&rearspar,upper&lowerpanel,ribs.Besides,itincludesMLGatta entsandpylonatta Thefront&rearspararecelltypeintegralmachiningstructures,thesparflangedeflectsthewingboxthematerialare7050－T7451&7085-T7651.The2-27ribsareintegralstructures,machinedfrom7050-T74517055—T7751，下蒙皮材料2324-T39。Theupper&lowerpanelsconsistofmachiningskinsandstringers.Thestringersaremachinedfromextrudingsection,theupperstringersare7055-T76511,thelowerstringersare2026－T3511.Theskinsaremachinedfrompre-drawingplates,thenshotpeeningforming.Theupperskinsare7055—T7751,thelowerskinsare2324-T39.撐桿接頭材料為Ti-6Al-4V，后交點接頭材料為7085，主起收放接頭材料為7050。輔助梁采用7050TheMLGattaentsconsistofMLGsupportfront&rearpivotpointfitting,MLGretractionfitting,sidestaypintlefittingandauxiliaryspar.TheMLGsupportfront&rearpivotpointfitting,MLGretractionfitting,sidestaypintlefittingaremachinedfromdieforgings.ThematerialofthefrontpivotpoinfittingandsidestaypintlefittingisTi-6Al-4V，therearpivotpointfitting’smaterialis7085,andtheMLGretractionfittingismadefrom7050.Theauxiliarysparismachinedfrom7050pre-drawing料為Ti-6Al-4V。Thepylonattaentsconsistofupperfitting,middlefitting,sidefittingandrearfitting.Thesefittingsaremachinedfromdieforgings,thematerialisTi-6Al-4V.固定前緣(TheLeadingTheouterwingleadingedgeisahalf-metalrivetingstructure,andconsistsofskinsanddummyplates.TheskinismadeofGFRP.Thedummyplatesconsistofreinforcedplatesandregularplates,allofthemaremachinedfromthickplate.Allthereinforcedplatesarearrangednormaltotherotationaxisoftheleading-edgeflap,anditworksthebearingofthetheleading-edgeflaptracks.固定后緣(TheTrailingTheouterwingtrailingedgeconsistsofinboardflapcabin,outboardflapcabinandaileroncabin.Theinboard&outboardflapcabinconsistoftheupper&lowerskinplate,dummyplate,fittings.Theupperskinplateisalloyplatestructure,thelowerskinplatecanbetakendown,sothelowerskinplateisalloyplate+ bstructure.Thedummyplateandfittingsaremadeof7050.Theaileroncabinconsistsoftheupper&lowerskinplate,dummyplate.Theupperskinplateis bstructure,thelowerskinplateisalloyplate+ bstructure.翼梢小翼Thewingletisthemixedstructurewhichthemostcompositematerialandtheleastaluminumalloy,itconsistsofwingbox,theleadingedgeandthetrailingedge.Thewingletandtheouterwingjointatthe27#rib,throughtheremovableboltsjointtheouterwingalongperipheral.前緣縫翼5段。通過齒輪齒條傳動機構(gòu)實現(xiàn)Theslatslocateontheuppersurfaceofthewing,thereare5slatsontheeachsideofwing.Theslatsgoandbackbytherackrunninggear.軌，2個主滑軌和2個輔助滑軌；25號縫翼各連接2個滑軌，均為主滑軌。Theslatisarivetedstructureofsinglesparwithmulti-ribs.Theyareconsistofinner&outerskin,frontspar,stringers,ribs,trailing-edgewedgeandtracks.Theleadingendoftracksarecombinedwiththeslats,thetrailingendissupportedbycarrigeinthewingfixedleadingedge.1#trackcombineswith4tracks,2maintracksand2secondarytracks;2#-5#trackscombinewith2trackseach,allofthemaremaintracks.12號縫翼結(jié)構(gòu)相似，無防冰管。3、4、5Thestructuresofthe1#and2#slataresimilar,noanti-icingtube.3#，4#and5#slatsarrangeanti-icingtube.后緣襟翼(Trailing-edgeTheflapoftheC919aircraftissingleslottedFowlerflap,thereisoneinboard&outboardflapintheeachsideofwing.Theinboard&outboardflapconsistofflapwingsurface,flapmechanismandflapfairings.Theflapwingsurfaceisdouble-sparCFRPstructer,theupper&lowerskinplateis bstructure.TheflapfairingisGFRPstructer.Themainpartsoftheflapmechanismaretitaniumalloy.副翼Theaileronisthemixedstructurewhichthemostcompositematerialandtheleastaluminumalloy,itconsistsofupperskin,co-curestructure(lowerskin+spar+endrib),innerribsandtrailingedgeparts.Thereare5hingefittingsand2drivefittingsinthefrontoftheaileronspar.擾流板51ThespoilersarearrangedattherearofthewingupperpanelandinfrontoftheflapsThereare5spoilersontheeachsideofwing,agroundspoilerintheinboard,and4multifunctionspoilersintheoutboard.擾流板采用碳纖維面板+Nomex蜂窩芯結(jié)構(gòu)。每塊擾流板有4個鉸頭和1個驅(qū)動器接頭。 bstructure.Thereare4hingefittingsand1fittingoneachspoiler惰化系統(tǒng)(Inerting系統(tǒng)組成和原理(SystemComposingandC247FA003惰化系統(tǒng)設(shè)計方案，C919飛機惰化系統(tǒng)2個獨立的子系統(tǒng)組成，分別是機AccordingtoC247FA003schemeofinertingsystem,theinertingSystemofC919Airplaneincludestwoindependentsections,anon-boardinertgasgenerationsystemandanitrogen-enrichedairdistributionsystem.Theon-boardinertgasgenerationsystem(OBIGGS)isalsobrokendownintothreesub-sections,aconditionedsupplyairsystem,anairseparationsystemandacontrol性。原理圖如圖1所示。ThedesignprincipleofinertingSystemofC919Airplaneistominimizethefuelflammabilitywithinertgasgeneratedthroughtheon-boardinertgasgenerationsystem,andSystemSchematicisshowninfigure1below.排排入大濾分配單向環(huán)控進閥換熱雙流切斷閥上游單向 火焰抑制溫空氣分離惰化系統(tǒng)1C919Fig.1C919AircraftSystem系統(tǒng)功能（System持在安全值之內(nèi)，以防止點火源發(fā)生燃油箱。其中機載制氮系統(tǒng)把來自環(huán)控系統(tǒng)的氣Theinertingsystemfunctionstodelivernitrogen-enrichedairintocentrewingofC919airplane，keeoxygenconcentrationoffuelullageatsafeleveltopreventfromexplodingcausedbyanyignitionsources.TheOBIGGSseparatesthebleedairfromECSintoNEAwithdifferentpurityandflowtoprovidethenitrogen-enricheddistributionsystem.Thenitrogen-enricheddistributionsystemequablydistributesNEAtofuel,makingoxygenconcentrationoffuelmeetthecertificationrequirement.系統(tǒng)接口(System惰化系統(tǒng)—環(huán)控系惰化系統(tǒng)—航電系惰化系統(tǒng)—結(jié)構(gòu)惰化系統(tǒng)—電氣系TheinertingSystemofC919AirplaneisinterfacedtheothersystemsasInertingsystem-air-coditioningInertingsystem-electrical燃油系統(tǒng)(Fuel系統(tǒng)組成和原理(SystemComposingand系統(tǒng)組成(SystemC919燃油系統(tǒng)(ATA28-燃油箱(ATA28-油箱通氣系統(tǒng)(ATA28-燃油箱除水系統(tǒng)(ATA28-燃油分配系統(tǒng)(ATA28-壓力加油/放油系統(tǒng)(ATA28-動力裝置供油系統(tǒng)(ATA28-APU供油系統(tǒng)(ATA28-燃油轉(zhuǎn)輸系統(tǒng)(ATA28-燃油測量與指示系統(tǒng)(ATA28-油量測量系統(tǒng)(ATA28-燃油壓力測量(ATA28-燃油溫度測量(ATA28-C919aircraftfuelsystemconsistsofthefollowingStorageSubsystem(ATA28-Fuel(ATA28-Vent(ATA28-12)DistributionSubsystem(ATA28-EngineFeed(ATA28-APUFeed(ATA28-FuelTransfer(ATA28-FuelPressureSensing(ATA28-FuelTemperatureSensing(ATA28-燃油系統(tǒng)設(shè)計原理(FuelSystemDesign方式。C919飛機燃油系統(tǒng)原理如圖2所示：C919aircraftfuelsystemhastakenaccountoftherequirementsofaircraftsafetyandcivilaviationrequirementsandadoptedthetraditionalscheme.AschematicdiagramdetailingthegenerallayoutofthefuelsystemisshowninFigure2.圖 C919飛機燃油系統(tǒng)構(gòu)型Fig.2C919AircraftFuelSystemC919C919C919飛機燃油測量系統(tǒng)采通道的測量系統(tǒng)構(gòu)建，利用RDC油箱內(nèi)傳感器信20ΜJ，從而保證飛機的安全性；C919aircraftfuelsystemadoptstheoverridefeedarchitecture,increasesthesystemreliabilityandensurestofeedthepowerplantsafely;ThepowerarchitecturetosupplytheC919aircraftfuelpumpisalternatingC919aircraftfuelmeasurementsystemusesadualchannelgaugingsystemconfigurationwithremotedataconcentratorstocaptureanddigitizein-sensor;Toensurefueltymeasurementsystemcanworkundersinglepointfailureconditionandenhancethereliabilityfordispatch,FRDCemploysdualchannelconfiguration.系統(tǒng)(StorageStoragesubsystemconsistsofFuel,VentandScavenge燃油箱(FuelTheumfuelcapacityofC919aircraftis19560kg,andtheminimumexpandingspaceoffuelis2%.69號肋為左右邊界。集油箱中油面一般保持在較Thecollectorisdelimitedbyrib#6andrib#9foreachwing.ThefuellevelincollectoralwaysremainhightoensurethefeedreliabilityforengineandAPU.Vent油箱內(nèi)壓力維持在結(jié)構(gòu)允許的范圍內(nèi),并防止燃油的虹吸和溢出。Theventsubsystemshouldensuretheinnerpressureoffuelmustbemaintainedwithintherangestructureenduredduringallaircraftoperations,includingfailureofhighlevelshutoffcontrolduringrefueloperations，itcanpreventoverboardfuelspillageorsiphoning.正常情況下，通氣系統(tǒng)應(yīng)確保燃油箱的壓力在-2psig～3.5psig umallowablepositivepressureis3.5psigandminimumallowablenegativepressureis–2psigduringnormaloperations,andpressuremustbemaintainedtolessthan10psiaboveatmosphericpressure,duringfailureofhighlevelshutoffcontrolduringrefueloperations.Thesurge aremaintainedatpressuresslightlyabovestaticatmosphericpressurebytheramairscoops.Anyfuelthatentersthesurgethroughtheventsystemwillbereturnedtothefuelthroughaflappercheckvalveinstalledatthebottomoftherib#22.Theventlineswithinthefuelwillbearrangedsothatatleastonelineisalwaysopen,providingunobstructedventingoftheinallnormalflightattitudes.Afloatventvalvewillbeinstalledonventinletswherevernecessarytopreventflowfromthefueltothesurgeduringpitchupandsideslipwingdownconditions.Aflamearrestorwillbeinstalledintheoverboardoutletfromeachsurge(ScavengeThescavengesubsystemwillbearrangedforeliminatingfuelandwaterwhereislow-lyinginthe,itcanpreventfuel structureerodedandicingduetotheaccumulationofwaterandensuretomeettherequirementoftheunusablefuel.(DistributionThedistributionsubsystemconsistsofrefueling/defuelingsubsystem,enginefeedsubsystemandAPUfeedsubsystem.燃油系統(tǒng)在右側(cè)機翼布有一個可直接連接地面加油設(shè)備的壓力加油點。每根加油管設(shè)油管的電磁閥切斷油流。Asinglepointpressurerefueladapterwillbeprovidedontherighthandsideoftheaircraftthatconnectsdirectlytothegroundpressurefuelingsystem.Refuelflowwillbecontrolledbyahydro-mechanicalshutoffvalvelocatedineachoftherefuellines.Apilotlinethatconnectstoahighlevelfloatvalvecanprovidecontroloftheshutoffvalve.AndasolenoidshutoffvalvewillbeinstalledinarefuelcontrollinetoprovideclosureoftherefuelshutoffvalvewhenelectricallycommandedbytheFuelty(EngineFeed油。正常工作時發(fā)動機壓力范圍：TVP＋5psig～50psig。對于吸力供油情況下，發(fā)動機Thefuctionofenginefeedsubsystemistoprovidefuelwhichmeetthepressureandflowrequirementtoenginewithinwholeflightenvelop.Theenginefeedsubsystemprovidesfueltotheenginesatleast5.0psihigherthanthetruevaporpressure(TVP)andatmost50pisgofthefuel,forallnormalgroundandflightaircraftoperatingmodes,andatleast3.8psiahigherthanthetruevaporpressure(TVP)forsuctionfeed.為發(fā)動機供油，兩泵同時運行，互為備份。同時也可由裝在翼內(nèi)的兩臺超控泵為發(fā)動機供控泵供油，主要由集油箱內(nèi)AC泵為發(fā)動機供油。當飛機縫翼收起后，自動開啟翼油箱內(nèi)此開始消耗翼油箱內(nèi)燃油，轉(zhuǎn)為由超控泵為發(fā)動機供油，直到超控泵壓力低于設(shè)定低壓值時，超控泵自動關(guān)閉，轉(zhuǎn)為由機翼油箱內(nèi)的AC泵為發(fā)動機供油。Eachenginehasaindependentfeedsystem.ThefuelfeedsubsystemconsistsoftwoACelectricpumpsskinmountedperwing ,servingasbothprimaryandsecondary.Bothpumpsruncontinuously.Theenginecanalsobefedfromthecenter pumps.Allpumpswillbeopenedto pre-checksincebeginning.Theoverridepumpswillberestrainedduringtake-offandclimbinguntiltheslatisdrawedback,andsimultaneouslythewing pumpsremainopening.Whenoperating,thecenter aredesignedtooverridethewing pumps,providingfueltotheenginedirectly.Thecenterpumpswillbenotstoppedautomaticallyuntiltheinletpressuredowntodesignatevalue,andwingpumpswillsupersedetofeedforengine.Acrossfeedshutoffvalvewillbeprovidedtoconnecttheleftwingandrightwingenginefeedsystem.Thecrossfeedfunctionwillbeprovidedtopermitfeedingfuelfrombothwingtoasingleengine,followingshutdownofoneengine,andalsotopermitcorrectionofminorlateralfuelimbalancesbytemporarilyfeedingbothenginesfromonlyonewing.APU(APUFeed55psig。對于情況下APU最低壓力要求TVP+5psigPerformancerequirementsfortheAPUfeedsystemshallbeidenticaltothosefortheenginefeedsystem,specificallythefuelsystemwillprovideadequatefuelflowtoensureatleast10psigandatmost55psigofthefuelforallnormalgroundandflightaircraftoperatingmodes,andatleast5.0psihigherthanthetruevaporpressure(TVP)forabnormaloperations.APUAPUTheAPUwillbefedfromthelefthandenginefeedlineduringnormaloperation.ADCpumpwillprovideasourceofpressurizedfuelforAPUstart.APU供油切斷閥都有熱釋壓能力，以防止由于供油管路內(nèi)的燃油熱膨脹導致管路建壓。ThermalreliefwillbeprovidedinAPUshutoffvalvetopreventpressurebuild-upinthefeedlineduetothermalexpansion.(FuelTransferC919Airplanehasthefunctionthattransferringfuelbetweendifferentonthe指示系統(tǒng)(IndicationIndicatingsubsystemconsistsoffueltyindicationsystem,pressureindicationsystemandfueltemperatureindicationsystem.Itcanachievefueltyindication,fueltemperatureindication,fuellowlevelwarning,fuelimbalancewarningandlowpressurewarningforfuelpumps.油量指示系統(tǒng)(FueltyIndication燃油LRM、加放油控制板以及連接電纜等組成。FueltyindicationsubsystemconsistsofFueltySensor,UnitwithCompensator,LowandHighLevelSensor,TemperatureSensor,FRDC,LRM,Refuel/DefuelPanelandHarnessetc.(PressureIndication系統(tǒng)功能(SystemC919飛機燃油系統(tǒng)功能如下 燃油裝置（APU）工作的任何機動飛行，都能向發(fā)動機和APU提供正常工作所需的燃油；C919aircraftfuelsystemhasthefollowingFuelTheprimaryfunctionofthefuelsystemistomaintainacontinuoussupplyfuelatarateandpressureestablishedforproperengineandauxiliarypowerunitfunctioningundereachlikelyoperatingBalancetheleftandrightfuel動力裝置系統(tǒng)組成和原理(SystemComposingand動力裝置系統(tǒng)采2CFM公司研發(fā)的新型渦輪風扇發(fā)LEAP-1C，并NEXCELLE公司提供配套短艙，采用翼吊式布局分別安裝在飛機兩側(cè)機翼下方。C919飛機動力裝置系統(tǒng)由下發(fā)動機短艙發(fā)動機燃油和控制系統(tǒng)發(fā)動機點火系統(tǒng)發(fā)動機空氣系統(tǒng)發(fā)動機系統(tǒng)動力裝置指示和告警系統(tǒng)排氣和反推系統(tǒng)發(fā)動機滑油系統(tǒng)發(fā)動機起動系統(tǒng)(ATA80)ThepropulsionsystemofC919consistsof2shipmentsofLEAPX-1CengineprovidedbyCFMwithnacelleprovidedbyNEXCELLE,whicharemountedunderthewings.LEAP-1Cisadualspoolturbofanhighbypassratioengine,whichconsistsoffollowingsystems:LEAP-X1CbasicControlandfuelIgnitionsystem(ATA74、BleedHandlingIndicationandwarningExhaustOilsystemStarting系統(tǒng)功能(SystemC919飛機動力裝置作為飛機最主要的動力能源系統(tǒng)，功能是在飛機的飛行包線和溫度包線Propulsionsystemisthemainenergysourceoftheaircraft.Itsmainfunctionistoprovideforward/reversethrust，powerextractionandbleedairtoaircraftthroughoutalltheflightandenvironmentenvelope.電氣線路互聯(lián)系統(tǒng)系統(tǒng)組成和原理(SystemComposingand為導線提供附加防護的材料包括導線絕緣、導線護套以及已經(jīng)帶電搭接連接的導管、或編ElectricalWiringInterconnectionSystemsmeansanywire,wiringdevice,orcombinationofthese,includingterminationdevices,installedinanyareaoftheairplaneforthepurposeoftransmittingelectricalenergy,includingdataandsignals,betweentwoormoreintendedterminationpoints.ThisincludesWiresandcables;Busbars;theterminationpointonelectricaldevices,includingthoseonrelays,interrupters,switches,contactors,terminalblocksandcircuitbreakers,andothercircuitprotectiondevices;connectors,includingfeed-throughconnectors;Connectoraccessories;Electricalgroundingandbondingdevicesandtheirassociatedconnections;Electricalsplices;Materialsusedtoprovideadditionalprotectionforwires,includingwireinsulation,wiresleeving,andconduitsthathaveelectricalterminationforthepurposeofbonding;Shieldsorbraids;Clampsandotherdevicesusedtorouteandsupportthewirebundle;Cabletiedevices;Labelsorothermeansofidentification;Pressure飛控作動系統(tǒng)(TheFightControlActuation系統(tǒng)組成和原理(SystemComposingandTheFightControlActuationSystemiscomposedof3sub-systems,theyarePrimaryFlightControlSystem,HighLiftSystem,andFlightDeckControlSystem.a)控制電子單元(REU)：其功能為為主舵面及擾流板作動器提供舵面位置伺服閉環(huán)，并提供作動器與REU的失效，REU與PCU通過法蘭盤與螺栓連接，隨PCU一起副翼作動器：其功能為為2個副翼舵面提供位置比例控制，每個舵面由2個電液作動器控升降舵作動器：其功能為為2個升降舵面提供位置比例控制，每個舵面由2個電液作動器方向舵作動器：其功能為為方向舵面提供位置比例控制，舵面由3多功能擾流板作動器：其功能為為8塊（4對）地面擾流板作動器：其功能為為2塊（1對）水平安定面配平作動器(HSTA)ThePFCASSystemiscomposedofthefollowingpiecesofhardwarewithcorrespondingDALs，eachofwhichisanLRU:RemoteElectronicsUnits:Itsfunctionistoperformsurfacepositionservo-loopclosureonprimary,spoiler,aswellasmonitoringforREU/Actuatorfailures.MotorControlElectronics:Itsfunctionistoperformvelocityservo-loopclosureandhigh-currentthree-phasemotorbridgecommutationfortheHorizontalStabilizerTrimActuator(HSTA)andmonitoringforMCEfailures.AileronPCUs:Itsfunctionistoprovideproportionalcontrolof2ailerons,using2electro-hydraulicactuatorspersurface.ElevatorPCUs:Itsfunctionistoprovideproportionalcontrolof2elevators,using2electro-hydraulicactuatorspersurface.RudderPCUs:Itsfunctionistoprovideproportionalcontrolofarudder,using3electro-hydraulicactuatorsonthesurface.MFSSpoilerPCUs:Itsfunctionistoprovideproportionalcontrolof8multi-functionspoilerpanels(4pairs),using1electro-hydraulicactuatorpersurface.GroundSpoilerActuators:Itsfunctionistoprovidecontrolof2GroundSpoiler(GS)PCUs(1pair),using1hydraulicactuatorpersurface.GroundSpoilerControlModule:Itsfunctionistoswitchthegroundspoileractuatortoeitheranextendstateorretractstate,basedonanACEcommandandHydraulicPressure.GroundSpoilerProximitySensor:ItsfunctionistoreporttheGroundSpoilerpositiontoFCSconfigurationannunciationandHorizontalStabilizerTrimActuator(HSTA):Itsfunctionistoprovidecontrolofamovablehorizontalstabilizerusingasinglelinearmulticircuitballscrewtypeelectromechanicalactuator.ThelayoutofthePFCASwillbeasshown3Fig.3MainFlyControlSystemAtthetwoendsofeachsurfacethereareskewsensorswhichareusedtodetectthesurfaceskew每側(cè)機翼前緣包括一個內(nèi)側(cè)縫翼面和四個外側(cè)縫翼面，內(nèi)側(cè)縫翼面兩端連接傾斜傳感器，用于面傾斜故障的探測。外側(cè)縫翼采用三個傳感器探測面傾斜，包括一根鋼索穿過四個縫翼面，一端連接傳感器；四個縫翼外端各有一個傳感器。Everywinghasaninboardslatandfouroutboardslats,withtwoskewsensorsattheendofinboardslatusedfordetectingtheskewfaultoftheinboardslatandthreeskewsensorsattheoutboardslatstodetecttheskewamongwhichacablewithoneendconnectingonesensorgoesthoughfourslatsandtheothertwoattheendoftheoutboardslats.在駕駛艙；兩個襟縫翼控制計算機，布置在中部EE艙；一個PDU動力控制組件（2個馬扭力管、角齒輪箱、扭力管支架、8個旋轉(zhuǎn)作動器，均布置在機翼后緣艙。HighLiftSystem’slayoutintheaircraftisshownonfigure4.TheflapsystemincludesaFSCL(4RVDTs)whichisinstalledinthecockpit.ThetwoFSECUsareinstalledinthemiddleEEbay.PDUpowercontrolunitwithtwohydraulicmotorsisinstalledinmiddleEEbay;The2dualflappositionsensors,8flapskewsensors,twoWTB,toquetubes,gearbox,steadybearings,8GRAsareallinstalledinthebackbayofthewing.縫翼系統(tǒng)包括一個PDU動力控制組件（2個馬達布置在鼓包內(nèi)；2個雙通道縫翼位置傳感器、10個縫翼傾斜傳感器、兩個翼尖剎車組件、扭力管、角齒輪箱、扭力管支架、20個SlatsystemincludesaPDUpowercontrolunitwithtwohydraulicmotorswhichisinstalledinthebellyfairing.The2dualslatpositionsensors,10slatskewsensors,2WTB,toquetubes,gearboxes,steadybearingsand20GRAsareallinstalledinthefrontbayofthewingorintheslats.4Fig.4HighLiftSystem’s空調(diào)系統(tǒng)(Air-conditioning系統(tǒng)架構(gòu)和組成(SystemArchitectureand節(jié)系統(tǒng)等組成。空調(diào)系統(tǒng)的組成方框圖見圖5。TheAirConditioningSystemofC919Airplaneincludes4independentsub-systems:AirDistributionSystem,CoolingSystem,TemperatureControlSystem,CabinPressureControlSystem.AirConditioningSystemSchematicisshowninthefigure圖 空調(diào)系統(tǒng)組成方框Figure AirConditioningSystem系統(tǒng)原理及安裝位置(SystemPrincipleand通過綜合空氣系統(tǒng)控制器對座艙通風、增壓、溫度的調(diào)節(jié)。空調(diào)系統(tǒng)原理圖見圖6。TheAirConditioningSystemmainlycomprisestheAirDistributionSystem,CoolingSystem,TrimAirSystem.TheIntegratedAirSystemController(IASC)controlsthecompartmentsventilation,pressure,andtemperaturetomeetthemainfunctions.TheSchematicsofAirConditioningSystemisshowingasbelowfigure6.圖 空調(diào)系統(tǒng)原理Fig.6TheSchematicsofAirConditioningTheCoolingsystemislocatedonthefuel adjacentarea,whichwouldbedescribedinthe制冷系統(tǒng)原理CoolingSystemTheenvironmentalcontrolsystemisusedtoregulatethehightemperatureandpressureofbleedairfromtheengines,theAPUoragroundsupplyunittothepropertemperature,pressureandhumidityconditioningair,inordertorealizethecockpitandcabinenvironmentadjusting.TheEnvironmentalCo