飞机燃油系统译文
飞机各部件英文翻译
飞机各部件英⽂翻译airliner 班机monoplane 单翼飞机glider 滑翔机trainer aircraft 教练机passenger plane 客机propeller-driven aircraft 螺旋桨飞机jet(aircraft) 喷射飞机amphibian ⽔陆两⽤飞机seaplane, hydroplane ⽔上飞机turbofan jet 涡轮风扇飞机turboprop 涡轮螺旋桨飞机turbojet 涡轮喷射飞机transport plane 运输机helicopter 直升机supersonic 超⾳速hypersonic ⾼超⾳速transonic 跨⾳速subsonic 亚⾳速Airbus 空中客车Boeing 波⾳Concord 协和Ilyusin 依柳⾟McDonald-Douglas 麦道Trident 三叉戟Tupolev 图波列夫aircraft crew, air crew 机组, 机务⼈员pilot 驾驶员, 机长co-pilot, second pilot 副驾驶员navigator 领航员steward 男服务员stewardess, hostess 空中⼩姐radio operator 报务员Bairliner 班机monoplane 单翼飞机glider 滑翔机trainer aircraft 教练机passenger plane 客机propeller-driven aircraft 螺旋桨飞机jet (aircraft) 喷射飞机amphibian ⽔陆两⽤飞机seaplane, hydroplane ⽔上飞机turbofan jet 涡轮风扇飞机turboprop 涡轮螺旋桨飞机turbojet 涡轮喷射飞机transport plane 运输机helicopter 直升机supersonic 超⾳速hypersonic ⾼超⾳速transonic 跨⾳速subsonic 亚⾳速Airbus 空中客车Boeing 波⾳Concord 协和Ilyusin 依柳⾟McDonald-Douglas 麦道Trident 三叉戟Tupolev 图波列夫hatch 舱⼝aeroengine, air engine 航空发动机navigation light 航⾏灯fuselage, body 机⾝nose 机头wing 机翼aileron 副翼wing flap 襟翼tail plane ⽔平尾翼starboard wing 右翼port wing 左翼pilot's cockpit 驾驶舱parachute 降落伞passenger cabin 客舱propeller 螺旋桨pressurized cabin 密封舱undercarriage 起落架undercarriage wheel 起落架轮elevator 升降舵radio navigation device ⽆线电导航设备radio directive device ⽆线电定向设备luggage compartment ⾏李舱(fuel) tank 油箱auxiliary (fuel) tank 副油箱main (fuel) tank 主油箱autopilot ⾃动驾驶仪ground crew 地勤⼈员airport 航空港, 民航机场airfield, aerodrome, airdrome 机场airport beacon 机场灯标airport meteorological station 机场⽓象站main airport building, terminal building 机场主楼emergency landing runway, forced landing runway 紧急着陆跑道taxiway 滑⾏跑道runway 跑道omnirange radio beacon 全向式⽆线电航空信标fuel depot 燃料库control tower 塔台tarmac 停机坪radio beacon ⽆线电信标boarding check 登机牌plane ticket 飞机票flight, flying 飞⾏bumpy flight 不平稳的飞⾏smooth flight 平稳的飞⾏ramp 扶梯altitude, height ⾼度air route, air line 航线extra flight 加班economy class, tourist class 经济座non-stop flight 连续飞⾏climbing, to gain height 爬升circling 盘旋forced landing 迫降connecting flight 衔接航班speed, velocity 速度ceiling 上升限度cruising speed 巡航速度top speed 最⾼速度first class 头等night service 夜航airsick 晕机direct flight, straight flight 直飞landing 着陆to rock, to toss, to bump 颠簸to taxi along 滑⾏to lose height, to fly low 降低to take off, take-off 起飞to board a plane, get into a plane 上飞机to get off a plane, alight from a plane 下飞机to face the wind 迎风飞机维修专业英语2008-08-10 12:00:16 AMUUcall ⽹络电话,注册就送60分钟话费飞机维修专业英语轮档挡好-- Chocks in地⾯电源设备接好--Ground power connected收到-- Roger现在关闭发动机--Shutting down engines准备牵引-- Ready for pushback所有舱门已关好--All doors checked closed松刹车-- Brakes off松刹车-- Release parking brakes刹车已松-- Brakes off刹车已松-- parking brake Released可以牵引 --Clear for pushback23号跑道起飞--Runway( or face)two three05号跑道起飞--Runway( or face)zero fie牵引完成 --Pushback complete刹车 --Brakes on刹车 --Set parking brake刹车刹好 --Brakes on刹车刹好-- Parking brake set准备启动1（或2）号发动机--Start number one(or two) 可以启动1（或2）号发动机--Clear number one(or two) 已经供⽓（如需⽓源车）--Pressure on启动结束 --Start complete断开地⾯设备-- Disconnect ground equipment插销移开 --Ping Remoed稍等 --Standby稍等启动-- Standby for start稍等推出-- Standby for pushback在左（或右）⽅打⼿势--Hand signal on the left(or right) aircraft crew, air crew 机组, 机务⼈员pilot 驾驶员, 机长co-pilot, second pilot 副驾驶员naigator 领航员steward 男服务员stewardess, hostess 空中⼩姐radio operator 报务员Bairliner 班机monoplane 单翼飞机glider 滑翔机trainer aircraft 教练机passenger plane 客机propeller-drien aircraft 螺旋桨飞机jet (aircraft) 喷射飞机amphibian ⽔陆两⽤飞机seaplane, hydroplane ⽔上飞机turbofan jet 涡轮风扇飞机turboprop 涡轮螺旋桨飞机turbojet 涡轮喷射飞机transport plane 运输机helicopter 直升机supersonic 超⾳速hypersonic ⾼超⾳速transonic 跨⾳速subsonic 亚⾳速Airbus 空中客车Boeing 波⾳Concord 协和Ilyusin 依柳⾟McDonald-Douglas 麦道Trident 三叉戟Tupole 图波列夫hatch 舱⼝aeroengine, air engine 航空发动机naigation light 航⾏灯fuselage, body 机⾝nose 机头wing 机翼aileron 副翼wing flap 襟翼tail plane ⽔平尾翼starboard wing 右翼port wing 左翼pilot"s cockpit 驾驶舱parachute 降落伞passenger cabin 客舱propeller 螺旋桨pressurized cabin 密封舱undercarriage 起落架undercarriage wheel 起落架轮eleator 升降舵radio naigation deice ⽆线电导航设备radio directie deice ⽆线电定向设备luggage compartment ⾏李舱(fuel) tank 油箱auxiliary (fuel) tank 副油箱main (fuel) tank 主油箱autopilot ⾃动驾驶仪ground crew 地勤⼈员airport 航空港, 民航机场airfield, aerodrome, airdrome 机场airport beacon 机场灯标airport meteorological station 机场⽓象站main airport building, terminal building 机场主楼emergency landing runway, forced landing runway 紧急着陆跑道taxiway 滑⾏跑道runway 跑道omnirange radio beacon 全向式⽆线电航空信标fuel depot 燃料库control tower 塔台tarmac 停机坪radio beacon ⽆线电信标boarding check 登机牌plane ticket 飞机票flight, flying 飞⾏bumpy flight 不平稳的飞⾏smooth flight 平稳的飞⾏ramp 扶梯altitude, height ⾼度air route, air line 航线extra flight 加班economy class, tourist class 经济座non-stop flight 连续飞⾏climbing, to gain height 爬升circling 盘旋forced landing 迫降connecting flight 衔接航班speed, elocity 速度ceiling 上升限度cruising speed 巡航速度top speed 最⾼速度first class 头等night serice 夜航airsick 晕机direct flight, straight flight 直飞landing 着陆to rock, to toss, to bump 颠簸to taxi along 滑⾏to lose height, to fly low 降低to take off, take-off 起飞to board a plane, get into a plane 上飞机to get off a plane, alight from a plane 下飞机to face the wind 迎风缩写 ABBREIATION LISTAA/C air conditioning 空⽓调节A/G air/groundA/L autoland ⾃动落地A/P autopilot ⾃动驾驶A/S airspeed 空速A/T autothrottle⾃动油门, adjustment/test 调整/测试ABNORM abnormal 不正常的AC alternating current 【电】交流电ACARS ARINC Communications Addressing and Reporting System ACCEL acceleration, accelerate 使增速ACM air cycle machine 空⽓循环机ADC air data computer ⼤⽓资料电脑ADF automatic direction finder ⾃动⽅位寻找器ADI attitude director indicator 姿态指⽰器ADP air drien pump, air drien hydraulic pump ⽓动液压泵AD adance 推进AFCS automatic flight control system 飞控系统AGL aboe ground leel 地标位AI anti-ice 防冰AIDS aircraft integrated data system 整合资料系统AIL aileron 副翼ALT altitude ⾼度ALTM altimeter ⾼度计ALTN alternate 交替的ALTNT alternate 交替的AMB ambient 环绕的AMM Airplane Maintenance Manual 修护⼿册ANN announcement 通告ANNUNC annunciator 通告器ANT antenna 天线AOA angle of attack 功⾓APB auxiliary power breaker 辅助的动⼒断电器APD approach progress display 接近⾏进显⽰APL airplane 飞机APPR approach 接近APPROX approximately 近乎APU auxiliary power unit 辅助的动⼒单元ARINC Aeronautical航空学的Radio Incorporated【美】有限责任的ARINC IO ARINC I/O errorARNC STP ARINC I/O UART data strip error 通⽤⾮同步收发传输器ASA autoland status annunciator ⾃动落地状况通告器ASP audio selector panel ⾳频选择⾯板ASYM asymmetrical ⾮对称的ATC air traffic control 空中交通管制ATC/DABS air traffic control/discrete address beacon systemATT attitude 姿态ATTND attendant 服务员AUTO automatic ⾃动装置的AUX auxiliary 辅助的AM airborne ibration monitor 空中震动监视器BB/CRS back course 回程BARO barometric ⽓压计的BAT battery 电池;蓄电池BFO beat扑动frequency oscillator 频率振汤器BITE built-in test equipment 装备⾃我测试BK brake 煞住(车)BKGRD background (⼲扰录⾳或⽆线电⼴播的)杂⾳BPCU bus power control unit 汇流排电⼒控制单元BRKR breaker 断电器BRT bright 发亮的BTB bus tie束缚breaker 汇流排联系断电器BTL bottle 瓶⼦CC/B circuit breaker 【电】断路器,断路开关C center 中央CADC central air data computer 中央⼤⽓资料电脑CAPT captain (飞机的)机长CB circuit breaker 【电】断路器,断路开关CCA central control actuator 中央控制致动器CCW counterclockwise 逆时针⽅向的CDU control display unit 控制显⽰器CH channel 频道CHAN channel 频道CHG change 改变CHR chronograph 记时器CHRGR charger 充电器CK check 检查CKT circuit 【电】电路;回路CL close 关闭;盖上;合上CLB climb 倾斜向上CLR clear 变乾净;变清楚CLSD closed 关闭的;封闭的;闭合的CMD command 命令CMPTR computer 电脑CNX cancelled 取消,废除;中⽌COL column 圆柱 (报纸的)栏,段COMM communication 通讯COMP compressor 压缩机COMPT compartment 隔间CON continuous 连续的,不断的COND condition 状态CONFG configuration 结构;表⾯配置CONFIG configuration 结构CONN connection 连接CONT control 控制CP control panel 控制⾯板CPCS cabin pressure control system 舱压控制系统CPS cycles per second 每秒循环CRS course ⽅向CRT cathode阴极ray射线 tube 阴极射线管CRZ cruise 巡航CSEU control system electronics unit 控制系统电⼦元件CT current电流transＦＯＲＭer变压器CTN caution 注意CTR center 中央CU control unit 控制元件CUST customer 顾客;买主CW clockwise 顺时针⽅向的CWS control wheel steering掌舵DDA drift漂移angleDADC digital air data computer 数位化⼤⽓资料电脑DC direct直系的,指挥currentDEC decrease减少, decrement减少率DECEL decelerate 降低速度DECR decrease 减少DEG degree 度数DEPR depressurize 洩压; 压下DEPT departure 离开;出发DEST destination ⽬标, ⽬的地DET detector 探测器DETNT detent (机械上的)⽌动装置;棘⽖DE deiation 误差;偏航DFDR digital flight data recorderDG directional⽅向的gyro回转仪罗盘DH decision决定height⾼度,海拔DIFF differential 依差别⽽定的;鉴别性的DIR direct 指挥DISC disconnect 使分离,分开,断开DISCH discharge 释放,排出(液体,⽓体等)DISCONT discontinued 停⽌,中断DISENG disengage 解开,解除;使脱离DISP dispatch 派遣DIST distance 距离;路程DK deck (船的) 舱⾯,甲板DME distance measuring equipment 测距仪DMU data management unit 资料管理单元DN down 向下DPCT differential protection current transＦＯＲＭer【电】变压器DR door 门DSCRT IO discrete分离I/O errorDSPLY display 显⽰DSPY display 显⽰EEADI electronic attitude director indicator 数位化姿态指⽰器ECON economy 节约, 经济ECS enironmental control system 环控系统EDP engine drien pump, engine hydraulic pump 引擎液压泵EEC electronic engine control 引擎电控EFDARS expanded flight data acquisition and reporting system EFI electronic flight instruments 电⼦化飞⾏仪表EFIS electronic flight instrument systemEGT exhaust gas temperature 排⽓尾温EHSI electronic horizontal situation indicator ⽔平状况⽅位指⽰器EICAS engine indicating and crew alerting system引擎状况警告指⽰ELEC electrical 与电有关的,电⽓科学的ELE eleation ⾼度;海拔EMER emergency 紧急情况ENG engage啮合,接合, engineENT entrance⼊⼝,门⼝, entryENTMT entertainment 娱乐EPC external power contactor 外电源接触器EPR engine pressure ratio 推⼒⽐EPRL engine pressure ratio limit 推⼒⽐范围EQUIP equipment 装备ERR error 错误ESS essential 必需品EAC eacuation 撤空;排泄物EBC engine ane and bleed control 引擎放⽓控制EXH exhaust 排出;排⽓EXT external 外部的EXTIN extinguish, extinguished 灭⽕器EXTING extinguishing 熄灭FF/D flight director 飞⾏引向器F/F fuel flow 燃油流量F/O first officerFAA Federal美国联邦 Aiation Administration⾏政机构FCC flight control computer 飞⾏控制电脑FCEU flight controls electronic unit 飞控电⼦单元FCU fuel control unit 燃油控制器FDR feeder 餵⾷器FIM Fault Isolation Manual 故障隔离⼿册FL flow 流量FL/CH flight leel changeFLD field(飞机)场,;(⼴阔的⼀⼤⽚)地(知识)领域;专业;(活动)范畴FLT flight (飞机的)班次FLUOR fluorescent 发亮的FMC flight management computer 飞⾏管理电脑FMS flight management system 飞⾏管理系统FREQ frequency 频率FRM Fault Reporting Manual 错误报告⼿册FSEU flap/slat electronic unit 副翼电控单元FT feet复, foot单英尺FWD forward 前⾯的GG/S glide slope, ground slope 下滑坡度GA go-around 重飞GB generator breaker 发电机断电器GCB generator circuit breaker 发电机断路器GCR generator control relay 发电机控制继电器GCU generator control unit 发电机控制组件GEN generator 发电机GHR ground handling relay 地⾯操作继电器GND ground 地⾯GP group 团体GPWS ground proximity warning system 地⾯接近警告GR gear 齿轮;传动装置; (飞机的)起落架GRD ground 地⾯GS ground speed 地速GSSR ground serice select relay 地⾯勤务选择继电器GSTR ground serice transfer relay 地⾯勤务转换继电器GW gross总量weight 总重HH/L high/low ⾼/低HDG heading 【航】航向HF high frequency ⾼频HORIZ horizontal ⽔平HP high pressure ⾼压HSI horizontal situation indicator ⽔平状况⽅位指⽰器HTR heater 加热器HYD hydraulic 液压的IIAS indicated airspeed 指⽰空速IDENT identification 识别;鉴定IDG integrated drie generatorIGN ignition 点⽕,发⽕;点⽕开关ILLUM illuminate, illuminated 被照明的;发光的ILS instrument landing system 仪降IMP imperial (度量衡)英制的IN in, input 输⼊INBD inboard 内侧的INC incorporated结合的, increase增⼤, increment增加INCR increase 增加IND indicator 指⽰器INFC interface 分界⾯INFLT inflight 飞⾏过程中的INHIB inhibit 抑制禁⽌INIT initiation ⼊门;开始实施INOP inoperatie 不活动的INPH interphone 对讲机INST instrument 仪器;仪表INT interphone 对讲机INTLK interlock 连结INTPH interphone 对讲机INTMT intermittent 时断时续的;周期性的IP intermediate pressure 中间的压⼒IRS inertial reference system 惯性参考系统IRU inertial惯性的reference unit 惯性参考组件ISLN isolation 隔离ISOL isolation 隔离ISI instantaneous瞬时的ertical speed indicator 垂直速度指⽰器MMCDP maintenance control display panel 修护控制显⽰⾯板MCP mode control panel 模式控制⾯板MCU modular模件concept观念 unitMDA minimum decision altitude 最⼩判断⾼度MIC microphone 扩⾳器;麦克风MIN minimum 最⼩量,最⼩数;最低限度MM Maintenance Manual 修护⼿册MOD module 组件;单元MON monitor 监视器;监控器MOT motion (机械的)装置,运转MPU magnetic pickup 检波器MSG message 信息MSTR master 主要的;总的MSU mode selector unit 模式选择组件MTG miles to go 英⾥MU management unit 管理组件MUX multiplexer 多路传输NN/A not applicable 可应⽤的NAC nacelle 引擎舱;⽓球吊篮NA naigation 导航NCD no computed data ⽆法计算资料NEG negatie 否定的; 反⾯的【电】负的,阴极的【数】负的NEUT neutral 中⽴的NLG nose landing gear ⿐轮起落架NO. number 数,数字NORM normal 正常的,正规的,标准的NRM normal 正常的,正规的,标准的NMEM RD non-olatile memory read error 故障读错误排除才能消除NMEM WR non-olatile memory write error 故障写错误排除才能消除O02 oxygen 氧⽓OBS obserer 观察员OK okay 对,很好地OPR operate 运转OPT option 选择权OPRN operation 操作OUT output 输出OUTBD outboard 外部的OHD oerhead 头顶(船舱)顶板OHT oerheat 过热ORD oerride 权⼒⾼於;优先於; 越过OXY oxygen 氧⽓PP/RST press to reset 压下清除故障P/S pitot⽪托管(流速计);⽪托静压管/static 静态的PA passenger address 客舱⼴播PASS passenger 旅客PCA power control actuator 电控致动器PCT percentage 百分⽐PDI pictorial deiation indicator 偏航图表⽰PES passenger entertainment娱乐systemPLA power leel anglePLT pilot (飞机等的)驾驶员,飞⾏员PMG permananet magnet generator 永磁发电机PNEU pneumatic ⽓动PNL panel 【电】配电盘;控电板POR point of regulation调节POS position, positie (电池的)阳极【数】正的PPOS present当前的出席的 positionPRESS pressure 压⼒PRG FLOW program flow error 流量程序错误PRIM primary ⾸要的,主要的PROC procedure 程序;⼿续;步骤PROG MEM ROM memory error 唯读记忆体错误PROJ projector 投射器PROT protection 保护,防护;PS pitot static ⽪托管(流速计);⽪托静压管PSI pounds per square inch 每平⽅⼨上的压⼒磅数PSS passenger serice system 客服系统PSU passenger serice unit 客服组件PTT push to talk 发话PTU power transfer unit 动⼒传送组件PWR power 动⼒QQAD quick-attach-detach 快拆卸;使分离QTS quarts ⼀夸脱的容器QTY quantity 数量RR/T rate of turn 回转速率R/W MEM RAM memory error 随机存取记忆体错误R right 右边的RA radio altimeter, radio altitude 雷达⾼度RAT ram air turbine 冲压驱动RCR recieer 接受RDMI radio distance magnetic indicator 磁场距离指⽰REC recorder 记录器RECIRC recirculate 再循环REF reference 参考REFRIG refrigeration 冷冻REG regulator 调节器REL release 释放,解放REP representatie 代表性的,典型的REQ required 必须的RES resere 储备RESSTART power interrupt restart error 动⼒中断重新起动错误RE reerse 倒退,使倒转RF right front 右前RH right hand 右⼿RLSE release 释放,解放RLY relay 【电】继电器RLY/SW relay/switchRMI radio magnetic indicator 磁场⽅位指⽰RMT OUT high-speed ARINC output error 汇流排输出错误RN right noseROT rotation 旋转RPM reolutions循环,(⼀)周期回转,旋转per minuteRPTG reporting 报导RR right rear 後⽅RST reset 重新设定RTO rejected丢弃takeoff起飞RUD rudder (飞机的)⽅向舵RW right wing 右翼RWY runway (机场的)跑道SSAM stabilizer trim/eleator asymmetry limit module尾舵飞操组件SAT static air temperature 静压空⽓温度SEC second 第⼆次SEI standby engine indicator 紧急直接引擎指⽰SEL select 选择SELCAL selectie calling 飞航呼叫SER serice 服务SG signal generator 信号产⽣器SLCTD selected 选择SLCTR selector 选择器SO shut off ale 关断阀SP speed 速度SPD speed 速度SPD BK speed brake 速煞SQL squelch 压扁SSB single side bandSTA station 驻地(各种机构的)站,所,STAB stabilizer 安定装置;安定翼STBY standby 备⽤STS system status 系统状况SURF surface 表⾯SW switch 开关SWITCH IN switch input errorSYNC synchronous 同步的SYS system 系统SYST system 系统TT/R thrust reerser 反推⼒器T.O. takeoff 起飞TACH tachometer 转速计TAI thermal热的anti-iceTAS true airspeed 真空速TAT total air temperature 总温TCC turbine case cooling 涡轮(机)冷却TE trailing edge 後缘(飞机的)襟翼,阻⼒板TEMP temperature 温度,⽓温TFR transfer 转换THR thrust 推⼒THROT throttle 节流阀THRSH threshold 门槛THRT thrust 推⼒THRU through 穿过;通过遍及,在...各处;在...之间,在...之中TIE bus tie系,拴,捆,扎汇流排联系TLA thrust leer angle 推⼒杆⾓度TMC thrust management computer 推⼒管理电脑TMS thrust management system 推⼒管理系统TMSP thrust mode select panel 推⼒选择⾯板TO TO/takeoff 起飞TOL tolerance 【机】公差,容限TR transＦＯＲＭer【电】变压器 rectifier【电】整流器TRP thrust rating panel 推⼒等级⾯板TUNE tuner (频率))调整器;【⽆】调谐器TURB turbine 涡轮(机)TURBL turbulent, turbulence【⽓】湍流;(⽓体等的)紊流UUBR utility有多种⽤途的;通⽤的bus relay 汇流排继电器UPR upperUSB upper side band 【机】传送带 (⽆线电的)波段,频带/NA ertical naigation 【经】纵向联合的导航/S ertical speed 垂直的速率ERT ertical 垂直的ERT SPD ertical speed 垂直的速率FY erify 验证G ertical gyro 垂直回转仪罗盘HF ery high frequency 超⾼频⽆线电IB ibration 震动LD alid 合法的;有效的L ale 【机】阀,活门OL olume 量;额OLT oltage 电压;伏特数OR HF omni range receier ⽅向⽆线识标OX oice 声⾳TR ideo tape reproducer (录⾳,录影的)播放装置WW/D wiring线路diagram图解W/W wheel well 轮舱WARN warning 警告;警报WG wing 机翼WHL wheel 轮⼦ ; 变换⽅向WHLS wheels 车轮WPT waypoint 位⼦点WSHLD windshield 挡风玻璃WX weather 天⽓WXR weather ⽓象雷达XX-CH cross channel 交叉频道X-CHAN cross channel 交叉频道XDCR transducer 变换器XMISSION transmission 传送XMIT transmit 发射XMTR transmitter 发射机XPNDR transponder 询答机YY/D yaw damper 阻尼器。
商用飞机专业术语库——燃油系统
中文词条 辅助动力装置 基本辅助动力装置 非基本辅助动力装置 1类辅助动力装置 2类辅助动力装置 辅助动力装置安装包 辅助动力装置系统 辅助动力装置舱 动力段 发动机压气机 负载压气机 进口导向叶片 附件齿轮箱 引气阀 喘振控制阀 滑油冷却器 电子控制单元 自检设备 排气温度 进气风门 进气风门作动器 拉杆 排气管 整合式消声器 冷却管 舱内通风冷却系统 风扇舱 核心舱 进气口 核心舱冷却气流控制 阀 发动机整流罩 风扇整流罩 前整流罩 侧整流罩 主动间隙控制 一体化叶盘 压气机出口压力 发动机附件 发动机总压比 外物损伤 高压关断阀 高压涡轮间隙控制 空气流量控制 加速/减速控制 自检 发动机构型塞 发动机指示和机组告 警系统 发动机接口控制单元 发动机振动监测 地面维护超控开关 反推整流罩 移动整流罩 安装节 最大爬升推力状态 最大连续推力状态
低压转速 高压转速 出口导向叶片 发动机进口压力 压气机出口总压 燃油消耗率 安装燃油消耗率 地面停车自检 全权限数字电子控制 器 转速控制 正常周期性自检 非易失性存储器 单发失效 奇偶 诊断和健康管理 永磁交流发电机 上电自检 本地发动机 滑油空气冷却器 碎屑探测器 发动机滑油油量 发动机滑油压力 发动机滑油温度 主燃滑油热交换器 伺服燃滑油热交换器 传动齿轮箱 惰化 惰化系统 进口隔离阀 臭氧转换器 门阀 过滤器 空气分离器 氧气传感器 双流量切断阀 机队平均可燃性暴露 可燃性暴露评估时间 危险大气 氧气析出 蒙特卡罗分析 检验压力 最大工作压力 爆破压力 有毒性反应浓度 防火系统 火灾探测系统 灭火系统 防爆系统 标准火焰 火源 名义点火源 潜在点火源 闪点 易燃液体点火源 潜在火区 易燃区
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航空术语专业对照
1、the airframe 机身,结构2、The front (fore) part 前部3、The rear (aft) part 后部4、port 左旋(舵)5、starboard 右旋(舵)6、the inboard engine or inboards 内侧发动机7、the outboard engine or outboards 外侧发动机8、the nose 机头9、the belly 腹部10、the skin 蒙皮11、the windscreen or windshield 风挡12、the wing 机翼13、the trailing edge 机翼后缘14、the leading edge 机翼前缘15、the wing tip 翼尖16、the control surface 操纵面17、ailerons 副翼18、flaps (inboard flap,outboard flap,leading edge flaps) 襟翼（内侧襟翼，外侧襟翼，前缘缝翼）19、spoilers (inboardoutboard spoiler)(spoiler downup) 阻力板，扰流板（内、外侧扰流板）（扰流板放下、打开）20、slats 缝翼21、elevators (elevator control tab) 升降舵（升降舵操纵片）22、rudder (rudder control tab) 方向舵（方向舵操纵片）23、flap angle 襟翼角24、flap setting 襟翼调整25、the full flap position 全襟翼位置26、a flapless landing 无襟翼着陆27、the landing gear 起落架28、stabilizer 安定面29、the nose wheel 前轮30、gear locked 起落架锁定31、the wheel well 起落架舱32、the wheel door 起落架舱门33、a tyre 轮胎34、to burst 爆破35、a deflated tyre 放了气的轮胎36、a flat tyre 走了气的轮胎37、a puncture 轮胎被扎破38、to extend the flaps (to retract the flaps) 放下襟翼（收上襟翼）39、gear extention (gear retraction) 起落架放下（起落架收上）40、The gear is jammed. 起落架被卡死。
飞机燃油系统
飞机系统 第二章 燃油系统
5）燃油内的微生物污染 除了上述无机物和有机物微粒杂质对燃油造成污染
外，有生命的微生物同样会造成危害。现今，在喷气 飞机油箱和机场油库的油罐内已发现一百多种微生物。 其中最普遍的是霉菌。
燃油系统一般由油箱系统、输油系统、加油系统、 放油系统、通气系统、增压系统及油量的测量指示系 统等组成。 简单燃油系统：15-38，P490 复杂燃油系统：15-42，P493
飞机系统 第二章 燃油系统
飞机系统 第二章 燃油系统
飞机系统 第二章 燃油系统
飞机系统 第二章 燃油系统
二、燃油的种类、特性及其对系统的影响
燃油是由具有不同饱和蒸汽压的碳氢化合物组成的。 当燃油蒸发时，具有高饱和蒸汽压的易挥发馏分汽 化快，剩余燃油的饱和蒸汽压就要降低。（越往后 蒸发越慢）
飞机系统 第二章 燃油系统
燃油中的轻馏分粒子（分子小,易蒸发），首先从表面 开始蒸发，然后从内部又有新的粒子升到表面上来。 因此当油箱是细高形时，轻馏分由内部升到表面速 度十分缓慢，燃油的蒸发便减弱；同理，油箱扁平 或搅拌燃油时，蒸发也就要加强。
飞机系统 第二章 燃油系统
燃油的蒸发性首先是由其化学成分，即馏分决定的，其 次与许多物理因素有关。 ⅰ、温度与高度(压力) ⅱ、汽/液相的容积比（该值大，Ps↓） ⅲ、油箱形状与振动搅拌 ⅳ、空气含量
飞机系统 第二章 燃油系统
燃油的蒸发性对系统影响主要有二个方面: 一是造成蒸发损失； 二是产生气穴现象（气塞）。 当飞机以超音速飞行时（M=2～3），飞机表面出现 强烈的气动加热，油箱内的燃油温度可达80~120℃， 若不采取措施，蒸发损失很严重。
飞机燃油系统英文版
Aircraft fuel systemName: XXXXXX ID: XXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXAbstract：Aircraft fuel system is a subsystem of many systems, its function is to store fuel, and ensure that the provisions of any state (such as various flight altitude, flight attitude), the engine can press the required pressure and flow continued uninterrupted fuel supply to the engine. In addition, the fuel system can also complete the rest of the aircraft cooling system, the balance of the aircraft, maintain aircraft center of gravity in the context of the provisions of other additional features. General civil aircraft fuel system including fuel tank system, add the oil drain system for the oil system, fuel tank ventilation pressurization system, fuel measurement systems, signal indicator system and the heat load system.Keywords:aircraft fuel；system For oil system ；Fuel tank ；The characteristics of fuel; The corrosion ; Safety and troubleshootingT he body of the PaperA:The composition of the fuel systemAs a fuel oil system, there must be at least fuel tanks, pipes, oil filter, cut-off valve and oil, scale, etc.The simplest of fuel oil supply system is to rely on gravity piston engine oil system.Tank has a height relative to the carburetor , to forme a pressure and make gasoline can reach the carburetor. Have a refueling at tank top, is also the fuel tank vent. A drain at the bottom of the tank, it is also a sewage outlet. There is a shut-off valve and fire damper before the oil filter before . Another start pump used to oil at startup. Fuel system consist of the fuel tank, fuel tank ventilation system, gas/oil emergency oil drain system, fuel supply system, air system and instructions/warning system, etc.B: The function of the fuel systema:Storage of fuel oilb:In stipulated flight conditions by the safe and reliable transfer fuel to the engine and APU by the safely and reliablyc:Adjust the center of gravity position, keep the balance and stress of the wing structured:Cooling accessories, as cooling sourceC:The characteristics of the fuel systema:The big fuel loadb:Oil supply securityc:can remove the oil pump not to put oil pump fast discharge , improve the maintenance performanced:The visualization of the fuel control panele:Avoid dead oilf:Using pressure refuelingg:Ventilation fuel tankh:Emergency oil discharge systemD:Demand for the fuel systema:To ensure the takeoff, landing, start, and high altitude can workefficiently, the fuel pump General installed in the bottom of oil tank,also must have the enough power when the engine driven pump fails toreplace it.b:When all booster pump fail, the tank still can supply the engine fuelrelying on gravity drainage or driven by the engine oil pump suctioneffect,c:Each tank has two booster pump at least . at least one pump to pumpout the fuel for any fuel load under normal flight attitude,d:Engine fuel system, should be supplied from the respective of oil tank.When emergency, one tank can supply all the engine .e:Fuel system should be could cross the oil, but can not be in the tankwith the overflow.f:Tank should be ventilated. Ventilation systems can provide sufficientventilation flow rate in any flight condition , and can prevent the fueloverflow from the vent pipe. Fuel tank can make ventilation system withpositive pressure, not a negative pressure, to ensure the booster pumpoperation is normal.g:With water collection and drainage facilities, to eliminate water andcontaminated the dirty oil. h:Oil sump tank, a ventilation should be taken to stop fuel to closedto overflow, collected after the fuel in the main fuel tank to most ofthe fuel consumption, by gravity flow into the main tank.i:Fuel pipe size should be guaranteed by maximum flow, and no sharp bendsin small radius bending and rising or falling, because these places willcause the vapor concentration causes the air plug.j:All internal and external fuel tank and accessories can be close to,in order to repair.E:Kinds of the tankAircraft fuel tank is used to store fuel needed for the plane. Aircraftfuel tank has three types, namely soft tank, fuel tank and tank structure.(1) soft tankSoft tank is made of oil resistant rubber, rubber and special clothsuch as agglutination and become, generally used in older planes and somesingle wing aircraft in the middle of the tank. At present, the soft tankin large passenger plane has rarely used.(2) the hard tankMade from anticorrosion ability strong aluminum manganese alloyenclosure, inside the suitcase is to prevent the oil sloshing perforatedbaffle, baffle plate can improve the strength and stiffness tank. At present, the hard tank often as auxiliary fuel tank in the middle of the large aircraft.(3) the structure of oil tankAircraft fuel tank adopting the structure, it is using the structure of the aircraft fuselage, the wings or tail element consists of the fuel tank directly, as shown in figure 2. Structure type is also known as the overall tank tank. Integral type oil tank is part of the aircraft structure, so in the place such as joints, structural fasteners and close to the flap should be properly sealed.Tank of the advantages of the structure can prevent the oil tank of inside of the ribs that shake, at the bottom of the ribs have a one-way valve, the oil from the wing tip to wing root. Structure can make full use of the characteristics of the fuel tank is the volume in the body, increase storage capacity, and reduce the weight of the aircraft.F:Tank of the arrangementA plane will arrange multiple fuel tank, that is, the central wing fuel tank and the fuel tank, also have on the outside of the main fuel tank aeration tank. Some aircraft are equipped with tail balancing tank and the auxiliary fuel tanks.(1) the central fuel tanksCentral mailbox is located in the central wing box, inside the fuel tank plate can prevent the fuel that shake when the plane fly in the motor. Flight, to reduce the bending moment of the wing root are, oil should be the first to use the central fuel tanks. When oil consumption in the empty tank, the tank full of fuel vapor. When fuel vapor concentration within the scope of fire (explosion) concentration, encounter sparks or high temperatures (static or through the fuel tank of the cable fault) can lead to fire explosion tank. To remove the danger of oil tank explosion fire, design the central tank must be considered when adding inert gas explosion suppression system or set the oil free dry cabin.Some aircraft using the other solution, that is, cancel the independence of the central fuel tanks, the airplane longitudinal profile separate central tank, with left and right main tank respectively, constitute the double tank layout. This kind of design while central tank inert gas explosion suppression system is omitted, but flying wing three tank layout is better than force.(2) the main tankWing tank according to the structure of the fuel tank is given priority to, generally called the left main tank no. 1 main tank, called in right main tank no. 2 main tank. Main tank surface usually have on gravity filler, the surface is equipped with several oil dipstick. The ribs inside the main tank can prevent oil sloshing occurs, at the bottom of the ribs have a one-way valve, make the oil from the wing tip to wing root.(3) the aeration tankAeration tank is located in the main tank outside and within the region near the wing tip. Aeration tank to fuel, not only for fuel tank ventilation.(4) balancing tankSome balancing tank in large aircraft. Balancing tank is installed in the tail section, usually installed in a horizontal stabilizer. In flight, fuel management systems according to need to fuel into (or out) balancing tank, adjust the position of the aircraft center of gravity decreased flat tail plane balancing point of view, reduce the balancing power, achieve the goal of improve aircraft fuel efficiency.(5) the central auxiliary fuel tanksThe auxiliary fuel tank as supplementary plane normal fuel tank system, used to enhance the aircraft's flight. The auxiliary fuel tank shape similar to standard shipping containers, housed in a plane's cargo hold before and after, using a special oil pipeline and ventilation pipe connected to the aircraft fuel system. In the middle of the configuration within the aircraft auxiliary fuel tank, should pay attention to the impact on the aircraft center of gravity.G:The causes of leakage and checka:The causes of leakage(1) incorrect joint connection, installation;(2) loose fasteners;(3) sealing ring damage;(4) sealant problem;(5) sealants damage;(6) the surface processing is undeserved, namely the surface grease, metal scrap, bristles, etc. These foreign secret agent cannot be together.(7) sealants mix and save is not correct. Sealant typically consists of two parts, i.e., substrate material and accelerator, if its mix proportion is not correct, it will affect the sealing effect, and sealant has a certain life, in a certain time after the sealant should test if can continue to use.(8) sealants used incorrectly. No sealant used in strict accordance with operating procedures likely to result in sealing effect becomes poor, lead to fuel leakage.b:Leakage inspection(1) pressure foaming agent test(2) hollow bolt bubble test(3) hollow bolt dyeing agent injection method(4) the air pressure testH:Fuel tank corrosion problemsWhen the tank suitable, bacteria will infested in oil. Hydrocarbons in the fuel oil and dissolved in the oil substances such as nitrogen, oxygen, sulfur, phosphorus, and offers all kinds of bacteria living in the material basis; The water in the fuel to provide the right environment for bacterial growth, bacteria normally live in fuel oil and water interface; Appropriate speed of temperature will accelerate the breeding of bacteria, the bacteria optimum growth te mperature is 25 ℃ ~ 30 ℃. Microorganism breeding in the fuel oil will cause the loss of fuel quality, forming dark mud sediment in the fuel. The sediment can cause great influence to the fuel system: plug the oil pump and oil filter, oil suction mouth cause oil supply system failure; Jam the fuel oil sensor, fuel quantity indicating system fault; Pollutants can not be clear in time and cause corrosion of tank. Studies have shown that microbial corrosion is the main form of corrosion in tank structure. In order to eliminate the influence of microbial contamination on the fuel system and the corrosion of tank, must destroy the bacteria breeding environment, controlling the growth speed. For now the only thing to do is control the moisture in the fuel.Moisture in the fuel oil will not only create a comfortable environment for bacterial growth, will also direct negative effects on the aircraft fuel system. So in the water system and installed in the fuel system is the tank water on a regular basis .I:Inspection of aircraft fuel system sealingThe check is in the condition of aircraft fuel tank filled with oil, make use of the ground air conditioning air conditioning, of bottle make tank pressurization to 24.5 kPa (0.25 KGF/com) conditions. Check whether the purpose is to ascertain the aircraft fuel tank pressurization line leakage and oil leaks oil.Open the ground air conditioning switch of bottle, then slowly open the ground of the plenum chamber gas switch, the aeration tank pressurization to the plane, when the air pressure inside the fuel tank rises to 24.5 kPa (0.25 KGF/cm2), turn off the ground Plenum chamber gas switch, switch off air conditioner bottles again, and then stay for 10 minutes, required the tank pressure drops should not exceed 1.9 kPa (0.02 KGF/cm2), the fuel tank and there should be no leakage of the junction.Inspection, pay special attention to check the 5, and 6 at the bottom of the tank, and the communicating pipe junction crack and leak. Because they are in engine compartment drier, easy to damage.Check finished, remove the plenum chamber on the ground, remove all the plug cover, jams, installed the fuselage tank pressure safety valve and the pipe joint, and then check the throttle lever is in the parking place, open fire protection switch, and switch on 1, 2, 3, oil pump work 2 ~ 3 minutes, to various fuel tank and pipe joint should not leak, the signal indicates a normal device.J: conclusionWriting a paper is a continuous learning process, from initial just when writing papers, fuzzy understanding of aircraft fuel system system to finally be able to have profound understanding of the problem, I realized the importance of practice in learning, only understand the theory before, without practice, understanding of knowledge is not enough clear, by doing this, I really realize the meaning of aircraft fuel system system, make of aircraft fuel system system I had a more profound understanding. All in all, through the paper, I deeply understand to want a thing well done is not so easy, need not only has the spirit of perseverance and never tired, but also need to have the ability to solve the problem. Treat to solve the problem, want to have patience, perseverance, be good at using knowledge and information to enrich yourself, make yourself get more progress, at the same time I also deeply aware that in dealing with a new problem, must from the overall consideration, do make the next step after step, in order to more effective. I see road, I will search up and down, in order to better life, I will keep learning, toward a higher goal. references[1] Alexandra Ebbinghaus,Peter Wiesen."Aircraft fuels andtheir effect upon engine emissions". Air and Space Europe . 2001[2] Raffi Babikian,Stephen P Lukachko,Ian A. Waitz.The historical fuel efficiency characteristics of regional aircraft from technological, operational, and cost perspectives. Journal of Air Transport Management .2002[3] Thomas H Bradley,Blake A.Moffitt,Dimitri N.Mavris,DavidE.Parekh."Development and experimentalcharacterization of a fuel cell powered aircraft". Journal of Power Sources . 2007[4] HaoLong,Xinmin Wang."Aircraft fuel system diagnosticfault detection through expert system". Conf.Proc,7thWorld Congress on Intelligent Control and Automation . 2008[5] Hao Long,Xinmin Wang."Application of aircraft fuel faultdiagnostic expert system based on fuzzy neural network". Conf.2009 WASE international conference on informationengineering . 2009[6] D. Preston."Aircraft Fuel Control Diagnostic Fault Detection through Expert Systems". Conf.Proc,IEEE International Symposium on IndustrialElectronics’’ 93 .[7] Juan F Jimenez,Jose M. Giron-Sierra,C. Insaurralde,M. Seminario."A simulation of aircraft fuel management system". Simulation Modelling Practice and Theory . 2007[8] Hao Long." Research of aircraft fuel fault detection ". .[9] Shujie Song."Research on aircraft integrated management system[10] : row understanding, Ye Anjian, HuaXingLai etc. Radar maintenance engineering. Wuhan: ZhongJun institute of radar[11] : Ma Shaomin, for integrated protection programs such as smelting. Beijing; Tian industry press, 1995。
燃油系统(fuelsystem)
-------------------------------------- 最新资料推荐 ----------------------------------燃油系统( fuel system )燃油系统(fuel system ) Fuel system.Txt lift up and put down is called weight lifting, lift up and put down is called weight. The head must have the courage, the rise should be emboldened. Learning to add, proud to be reduced, the opportunity to travel, in addition to lazy to. The three problems of life: thinking, love, Unrequited love. First, training objective: 1) master the rapid diagnosis method of oil pressure relief method and circuit fault 2) master the maintenance method of electric fuel pump and fuel injector fuel system Two, the content of training: 1) the oil pressure relief system 2) detection of vehicle fuel system 3) electric fuel pump inspection and testing 4) inspection and testing of electromagnetic injector Three, training equipment, tools and materials Santana 2019, the fuel pump assembly, fuel injector assembly. The oil pressure gauge, digital multimeter, manual vacuum pump, injector cleaning machine, common tools, with scales, containers, cotton yarn, gasoline, wire etc. Four, training operation: 1, the oil pressure relief system From the entrance of the fuel filter pressure relief pipe joint The pressure relief valve pressure relief The dynamic pressure relief Theinjector with pressure relief The manual vacuum pump with pressurerelief Detection of 2, the fuel system of the car 1) in the power supply voltage is not less than 12V, switch off the ignition, remove the battery strap. 2) pressure gauge pressure relief after loading of gasoline, gasoline pump power and short circuit. 3) put on the battery strap, the ignition switch is in the ON position, the gasoline pump pressure test. If the pressure is too high, then replace the pressure regulator; if the pressure is too low, then check the fuel pump, fuel filter and pressure regulator for leaks.4) the ignition switch for the OFF position, remove the fuel pump short wiring. 5) to start the engine, the idle state of the pressure measuring system. If the oil pressure of the system is not in the specified range, check the vacuum tube and pressure regulator. 6). Remove vacuum hose from the oil pressure regulating, plug the hose. The test pressure shall comply with the provisions. 7) off after five minutes to check the oil pressure, such as drop, check the fuel pumpa nd pressure regulator for leaks. 8) pressure relief, remove the strap, remove the oil pressure gauge. 9) after loading complex leak. 3, the fuel pump test Test the working condition of the fuel pump should ensure the battery voltage is normal, thegasoline最新资料推荐pump fuse is normal, normal gasoline filter. 1) gasoline pumpcircuit check ON (ignition means connected to the ignition switch), gasoline pumps hould be able to hear the startup sound, if a finger pinch pipeline should be able to feel the pressure. If the fuel pump does not start, should check the fuel pump, gasoline and fuel pumpr elay control circuit. OFF (meaning the ignition switch off ignition), fuel pumpr elay must have action, otherwise check the fuel pumpr elay line, if the line is normal, the replacement of fuel pump relay. If the fuel pump relay, gasoline pump is still not working. The ignition switch is closed, with a multimeter measuring gasoline pump power supply voltage on the conductor, the voltage value is about normal battery voltage (about 12V). If the voltage does not reach the specified value, you need to find and remove the fuel pump circuit circuit fault; if the voltage reaches the specified value, take the lead wire colleagues found no gasoline pump circuit, that electric fuel pump failure, should check the replacement of fuel pump. 2) test gasoline pump The ignition OFF from gasoline pump electric plug. The resistance meter gasoline pump coil resistance, if not within the specified scope, then replace the gasoline pump assembly. The power supply to the gasoline pumpp lus 12V (note the polarity), check the running condition of the gasoline pump. If not normal, replace gasoline pump assembly. Note: this experiment should be completedto avoid burning gasoline pump coil in 10S, while the gasolinepumpa way from the battery. 3) measuring gasoline pump supply The ignition OFF The pressure relief after receiving the pressure gauge on the oil pipe. The hose to the oil return pipe, and into the cup. The use of joint wire shorted fuel pumpr elay contacts and battery positive terminal, the steam pumpo peration system hydraulic power. The empty cup. The switch on the gasoline pump, make it work. Pump oil measurement within the prescribed time, compared to a predetermined value. If you do not reach the minimum amount of oil, possible causes for the pipeline bending or obstruction, gasoline pump failure etc.. Detection of4. injector 1)injector inspection, (1) check the working condition of the fuel injector when the engine is running, touch the injector or use a stethoscope to check the fuel injector, to see whether the machine work is consistent with the engine speed. If not normal, check the fuel injection signal ECM output. If the fuel injector is difficultto close, the method can be used tocheck off the fire. Check the action to be fast, failure or long最新资料推荐time off cylinder will accelerate the three element catalytic converter. (2) check the fuel injector without plugging andleakage. The ignition OFF, from all the injector plug. The oiling is the oil pressure gauge, short pump power of the gasoline gasoline pump operation, the oil pressure is set up. The one by one to the fuel injector for 12V pulse, while listening to the sound is normal. Note: if the injector is low resistance type, it should be ranked a resistance of about 10 ohmsr esistance in the circuit, in order to protect the injector coil. The power supply to the fuel injector, the hydraulic pressure should be decreased, or the phenomenon of fouling of the injector. If the fuel injector fuel injection system andno pressure drop, the injector leaks. Remove all the injector observation, black marks of spray hole leakage of fuel injector.(3) injector safety check ignition resistance OFF, disengaged from the injector plug, the injector coil resistance measurement. Beyond the technical scope, then replace the. (4) fuel injection quantity, atomization and leakage may be inspected by injector test bench, in accordance with the instructions on the steps of the project, testing. If there is no injector test bench, can be carried out according to thefollowing methods: The fuel distribution pipe and fuel injectors to remove the hose, the fuel distribution pipe and filter the export import reliably connected, while the other one hosepressure regulator to the oil inlet and return pipe.The ignition ON, running short circuit electric fuel pump to establish hydraulic system. The observation of the injector has no oil leakage, no more than 1 drops per minute, or replace injector. The ignition plug from OFFi njector. The injector is placed in a high power cylinder, 15S for 12V to the injector (note the supply current should not exceed 1A). The atomization of fuel injection to observe the colleagues measured and recorded injection volume. Each injector is repeated 2-3 times. The error between the standard and the injection volume of theinjector should meet the requirements, cleaning or replacement or injector. If the injection quantity is greater than or less than the specified value, check the hydraulic system. 2)injector circuit check Check the power supply (1) Theignition OFFi njector plug off. The ignition voltage meter ON, the negative form of ground, the two terminal card pen has test harness plug, wherein one terminal of the voltage should be 12V. Otherwise check the ignition and relay it to the wire harness connection between batteries. (2) check the computer control最新资料推荐terminal of the fuel injector is pulsed power components, in order to avoid the damage of electronic circuit in ECM, in the ECMin jector ground is good. 1 made a series of about 330 ohms resistor diode test lamp. In the case of OFF ignition, theconnected with the battery cathode, lamp test harness plug connected asinjector plug on all cylinders arenot bright, Check the fuel injection control and sensor input signal correlation (such as the crankshaft and camshaft position sensor) If the check part when the injector test lamp not shining, in the end of the examination control injector end connection, check the control power transistor computer in ECM. We can do an experiment to determine whether the injection signal: remove wiring injector control end to ECM, the injector pulse artificial ground. But after loading complex with starter when starting the fuel injector fuel injection, ECMAs hows no output signalinjection. Removet he ECM,w ork inspection cover transistor is normal. If the transistor is good, then the ECM fault. 5, cleaning thefuel injector The main fault injector when fouling, causing fuel injection quantity significantly reduced. Because some gasoline quality is not very good, so it should be regular cleaning and replacement of fuel injector. If the fuel system is equipped with cathode diode type lamp is anode and computer control shown in figure 1-20. The connectivity starter, two tube type lights should be flashing. Otherwise the control injector plug end to ECMb etween the lines and connections. If the test lightcold start injector, and fuel injectors to ensure that it is clean. The commonly used vehicle washer or ultrasonic cleaning instrument for injector cleaning. If none of the above equipment, can also pass the 12V voltage to the injector (note that the current is not too large), and with a clean 30N/cm2 high-pressure air reverse blowing injector to complete the cleaning work. Be careful ：1) do not put the injector immersed in the cleaning solvent, it can not achieve the cleaning effect, may also damage the injector. 2) do not use wire brush, tube type cleaner, toothpicks or other cleaning utensils to poke the injector clogging. 3) can not be scraping, hinge pin hole measurement. 4) should be cleaning the gasoline tank and tubing while cleaning the injector, and replace gasoline filter.。
飞机燃油系统
飞机燃油系统【摘要】飞机燃油系统是飞机上众多系统中的一个子系统，它的功用是储存燃油，并保证在规定的任何状态（如各种飞行高度、飞行姿态）下，均能按发动机所要求的压力和流量向发动机持续不间断地供油。
此外，燃油系统还可以完成冷却飞机上其他系统、平衡飞机、保持飞机重心于规定的范围内等附加功能。
民用飞机燃油系统一般包括燃油箱系统、加放油系统、供输油系统、油箱通气增压系统、燃油测量系统、信号指示系统和热负载系统。
关键词：飞行高度、燃油系统、加放油系统、供输油系统、信号指示系统、热负载Abstract：Aircraft aircraft fuel system is a subsystem of many systems, its function is to store fuel, and ensure that the provisions of any state (such as various flight altitude, flight attitude), the engine can press the required pressure and flow continued uninterrupted fuel supply to the engine. In addition, the fuel system can also complete the rest of the aircraft cooling system, the balance of the aircraft, maintain aircraft center of gravity in the context of the provisions of other additional features. General civil aircraft fuel system including fuel tank system, add the oil drain system for the oil system, fuel tank ventilation pressurization system, fuel measurement systems, signal indicator system and the heat load system.Keywords: aircraft fuel system; Development目录1 飞机燃油系统的概述 (2)1.1燃油系统的功用 (2)1.2燃油系统的特点 (2)2飞机燃油系统的组成 (3)2.1燃油通气系统 (4)2.1.1燃油箱通气系统的作用 (4)2.1.2通气系统的组成和工作原理 (4)2.2加油系统 (5)2.3应急放油系统 (6)2.4供油系统 (7)2.4.1飞机的供油方式 (7)2.4.2燃油测量系统 (8)2.5燃油箱油量指示系统 (9)3航空燃油 (11)3.1航空汽油 (11)3.2航空煤油 (11)4燃油系统附件 (12)4.1燃油箱 (12)4.2增压泵 (12)4.3引射泵 (12)5燃油测量系统的发展趋势 (13)结束语 (14)谢辞 (14)文献 (16)1 飞机燃油系统的概述飞机燃油系统是飞机上众多系统中的一个子系统，它的功用是储存燃油，并保证在规定的任何状态（如各种飞行高度、飞行姿态）下，均能按发动机所要求的压力和流量向发动机持续不间断地供油。
飞机各部件英文翻译
飞机各部件英文翻译airliner 班机monoplane 单翼飞机glider 滑翔机trainer aircraft 教练机passenger plane 客机propeller-driven aircraft 螺旋桨飞机jet(aircraft) 喷射飞机amphibian 水陆两用飞机seaplane, hydroplane 水上飞机turbofan jet 涡轮风扇飞机turboprop 涡轮螺旋桨飞机turbojet 涡轮喷射飞机transport plane 运输机helicopter 直升机supersonic 超音速hypersonic 高超音速transonic 跨音速subsonic 亚音速Airbus 空中客车Boeing 波音Concord 协和Ilyusin 依柳辛McDonald-Douglas 麦道Trident 三叉戟Tupolev 图波列夫aircraft crew, air crew 机组, 机务人员pilot 驾驶员, 机长co-pilot, second pilot 副驾驶员navigator 领航员steward 男服务员stewardess, hostess 空中小姐radio operator 报务员Bairliner 班机monoplane 单翼飞机glider 滑翔机trainer aircraft 教练机passenger plane 客机propeller-driven aircraft 螺旋桨飞机jet (aircraft) 喷射飞机amphibian 水陆两用飞机seaplane, hydroplane 水上飞机turbofan jet 涡轮风扇飞机turboprop 涡轮螺旋桨飞机turbojet 涡轮喷射飞机transport plane 运输机helicopter 直升机supersonic 超音速hypersonic 高超音速transonic 跨音速subsonic 亚音速Airbus 空中客车Boeing 波音Concord 协和Ilyusin 依柳辛McDonald-Douglas 麦道Trident 三叉戟Tupolev 图波列夫hatch 舱口aeroengine, air engine 航空发动机navigation light 航行灯fuselage, body 机身nose 机头wing 机翼aileron 副翼wing flap 襟翼tail plane 水平尾翼starboard wing 右翼port wing 左翼pilot's cockpit 驾驶舱parachute 降落伞passenger cabin 客舱propeller 螺旋桨pressurized cabin 密封舱undercarriage 起落架undercarriage wheel 起落架轮elevator 升降舵radio navigation device 无线电导航设备radio directive device 无线电定向设备luggage compartment 行李舱(fuel) tank 油箱auxiliary (fuel) tank 副油箱main (fuel) tank 主油箱autopilot 自动驾驶仪ground crew 地勤人员airport 航空港, 民航机场airfield, aerodrome, airdrome 机场airport beacon 机场灯标airport meteorological station 机场气象站main airport building, terminal building 机场主楼emergency landing runway, forced landing runway 紧急着陆跑道taxiway 滑行跑道runway 跑道omnirange radio beacon 全向式无线电航空信标fuel depot 燃料库control tower 塔台tarmac 停机坪radio beacon 无线电信标boarding check 登机牌plane ticket 飞机票flight, flying 飞行bumpy flight 不平稳的飞行smooth flight 平稳的飞行ramp 扶梯altitude, height 高度air route, air line 航线extra flight 加班economy class, tourist class 经济座non-stop flight 连续飞行climbing, to gain height 爬升circling 盘旋forced landing 迫降connecting flight 衔接航班speed, velocity 速度ceiling 上升限度cruising speed 巡航速度top speed 最高速度first class 头等night service 夜航airsick 晕机direct flight, straight flight 直飞landing 着陆to rock, to toss, to bump 颠簸to taxi along 滑行to lose height, to fly low 降低to take off, take-off 起飞to board a plane, get into a plane 上飞机to get off a plane, alight from a plane 下飞机to face the wind 迎风飞机维修专业英语2008-08-10 12:00:16 AMUUcall 网络电话,注册就送60分钟话费飞机维修专业英语轮档挡好-- Chocks in地面电源设备接好--Ground power connected 收到-- Roger现在关闭发动机--Shutting down engines准备牵引-- Ready for pushback所有舱门已关好--All doors checked closed松刹车-- Brakes off松刹车-- Release parking brakes刹车已松-- Brakes off刹车已松-- parking brake Released可以牵引 --Clear for pushback23号跑道起飞--Runway( or face)two three05号跑道起飞--Runway( or face)zero fie牵引完成 --Pushback complete刹车 --Brakes on刹车 --Set parking brake刹车刹好 --Brakes on刹车刹好-- Parking brake set准备启动1（或2）号发动机--Start number one(or two) 可以启动1（或2）号发动机--Clear number one(or two) 已经供气（如需气源车）--Pressure on启动结束 --Start complete断开地面设备-- Disconnect ground equipment插销移开 --Ping Remoed稍等 --Standby稍等启动-- Standby for start稍等推出-- Standby for pushback在左（或右）方打手势--Hand signal on the left(or right)aircraft crew, air crew 机组, 机务人员pilot 驾驶员, 机长co-pilot, second pilot 副驾驶员naigator 领航员steward 男服务员stewardess, hostess 空中小姐radio operator 报务员Bairliner 班机monoplane 单翼飞机glider 滑翔机trainer aircraft 教练机passenger plane 客机propeller-drien aircraft 螺旋桨飞机jet (aircraft) 喷射飞机amphibian 水陆两用飞机seaplane, hydroplane 水上飞机turbofan jet 涡轮风扇飞机turboprop 涡轮螺旋桨飞机turbojet 涡轮喷射飞机transport plane 运输机helicopter 直升机supersonic 超音速hypersonic 高超音速transonic 跨音速subsonic 亚音速Airbus 空中客车Boeing 波音Concord 协和Ilyusin 依柳辛McDonald-Douglas 麦道Trident 三叉戟Tupole 图波列夫hatch 舱口aeroengine, air engine 航空发动机naigation light 航行灯fuselage, body 机身nose 机头wing 机翼aileron 副翼wing flap 襟翼tail plane 水平尾翼starboard wing 右翼port wing 左翼pilot"s cockpit 驾驶舱parachute 降落伞passenger cabin 客舱propeller 螺旋桨pressurized cabin 密封舱undercarriage 起落架undercarriage wheel 起落架轮eleator 升降舵radio naigation deice 无线电导航设备radio directie deice 无线电定向设备luggage compartment 行李舱(fuel) tank 油箱auxiliary (fuel) tank 副油箱main (fuel) tank 主油箱autopilot 自动驾驶仪ground crew 地勤人员airport 航空港, 民航机场airfield, aerodrome, airdrome 机场airport beacon 机场灯标airport meteorological station 机场气象站main airport building, terminal building 机场主楼emergency landing runway, forced landing runway 紧急着陆跑道taxiway 滑行跑道runway 跑道omnirange radio beacon 全向式无线电航空信标fuel depot 燃料库control tower 塔台tarmac 停机坪radio beacon 无线电信标boarding check 登机牌plane ticket 飞机票flight, flying 飞行bumpy flight 不平稳的飞行smooth flight 平稳的飞行ramp 扶梯altitude, height 高度air route, air line 航线extra flight 加班economy class, tourist class 经济座non-stop flight 连续飞行climbing, to gain height 爬升circling 盘旋forced landing 迫降connecting flight 衔接航班speed, elocity 速度ceiling 上升限度cruising speed 巡航速度top speed 最高速度first class 头等night serice 夜航airsick 晕机direct flight, straight flight 直飞landing 着陆to rock, to toss, to bump 颠簸to taxi along 滑行to lose height, to fly low 降低to take off, take-off 起飞to board a plane, get into a plane 上飞机to get off a plane, alight from a plane 下飞机to face the wind 迎风缩写 ABBREIATION LISTAA/C air conditioning 空气调节A/G air/groundA/L autoland 自动落地A/P autopilot 自动驾驶A/S airspeed 空速A/T autothrottle自动油门, adjustment/test 调整/测试ABNORM abnormal 不正常的AC alternating current 【电】交流电ACARS ARINC Communications Addressing and Reporting SystemACCEL acceleration, accelerate 使增速ACM air cycle machine 空气循环机ADC air data computer 大气资料电脑ADF automatic direction finder 自动方位寻找器ADI attitude director indicator 姿态指示器ADP air drien pump, air drien hydraulic pump 气动液压泵AD adance 推进AFCS automatic flight control system 飞控系统AGL aboe ground leel 地标位AI anti-ice 防冰AIDS aircraft integrated data system 整合资料系统AIL aileron 副翼ALT altitude 高度ALTM altimeter 高度计ALTN alternate 交替的ALTNT alternate 交替的AMB ambient 环绕的AMM Airplane Maintenance Manual 修护手册ANN announcement 通告ANNUNC annunciator 通告器ANT antenna 天线AOA angle of attack 功角APB auxiliary power breaker 辅助的动力断电器APD approach progress display 接近行进显示APL airplane 飞机APPR approach 接近APPROX approximately 近乎APU auxiliary power unit 辅助的动力单元ARINC Aeronautical航空学的Radio Incorporated【美】有限责任的ARINC IO ARINC I/O errorARNC STP ARINC I/O UART data strip error 通用非同步收发传输器ASA autoland status annunciator 自动落地状况通告器ASP audio selector panel 音频选择面板ASYM asymmetrical 非对称的ATC air traffic control 空中交通管制ATC/DABS air traffic control/discrete address beacon system ATT attitude 姿态ATTND attendant 服务员AUTO automatic 自动装置的AUX auxiliary 辅助的AM airborne ibration monitor 空中震动监视器BB/CRS back course 回程BARO barometric 气压计的BAT battery 电池;蓄电池BFO beat扑动frequency oscillator 频率振汤器BITE built-in test equipment 装备自我测试BK brake 煞住(车)BKGRD background (干扰录音或无线电广播的)杂音BPCU bus power control unit 汇流排电力控制单元BRKR breaker 断电器BRT bright 发亮的BTB bus tie束缚breaker 汇流排联系断电器BTL bottle 瓶子CC/B circuit breaker 【电】断路器,断路开关C center 中央CADC central air data computer 中央大气资料电脑CAPT captain (飞机的)机长CB circuit breaker 【电】断路器,断路开关CCA central control actuator 中央控制致动器CCW counterclockwise 逆时针方向的CDU control display unit 控制显示器CH channel 频道CHAN channel 频道CHG change 改变CHR chronograph 记时器CHRGR charger 充电器CK check 检查CKT circuit 【电】电路;回路CL close 关闭;盖上;合上CLB climb 倾斜向上CLR clear 变乾净;变清楚CLSD closed 关闭的;封闭的;闭合的CMD command 命令CMPTR computer 电脑CNX cancelled 取消,废除;中止COL column 圆柱 (报纸的)栏,段COMM communication 通讯COMP compressor 压缩机COMPT compartment 隔间CON continuous 连续的,不断的COND condition 状态CONFG configuration 结构;表面配置CONFIG configuration 结构CONN connection 连接CONT control 控制CP control panel 控制面板CPCS cabin pressure control system 舱压控制系统CPS cycles per second 每秒循环CRS course 方向CRT cathode阴极ray射线 tube 阴极射线管CRZ cruise 巡航CSEU control system electronics unit 控制系统电子元件CT current电流transＦＯＲＭer变压器CTN caution 注意CTR center 中央CU control unit 控制元件CUST customer 顾客;买主CW clockwise 顺时针方向的CWS control wheel steering掌舵DDA drift漂移angleDADC digital air data computer 数位化大气资料电脑DC direct直系的,指挥currentDEC decrease减少, decrement减少率DECEL decelerate 降低速度DECR decrease 减少DEG degree 度数DEPR depressurize 洩压; 压下DEPT departure 离开;出发DEST destination 目标, 目的地DET detector 探测器DETNT detent (机械上的)止动装置;棘爪DE deiation 误差;偏航DFDR digital flight data recorderDG directional方向的gyro回转仪罗盘DH decision决定height高度,海拔DIFF differential 依差别而定的;鉴别性的DIR direct 指挥DISC disconnect 使分离,分开,断开DISCH discharge 释放,排出(液体,气体等)DISCONT discontinued 停止,中断DISENG disengage 解开,解除;使脱离DISP dispatch 派遣DIST distance 距离;路程DK deck (船的) 舱面,甲板DME distance measuring equipment 测距仪DMU data management unit 资料管理单元DN down 向下DPCT differential protection current transＦＯＲＭer【电】变压器DR door 门DSCRT IO discrete分离I/O errorDSPLY display 显示DSPY display 显示EEADI electronic attitude director indicator 数位化姿态指示器ECON economy 节约, 经济ECS enironmental control system 环控系统EDP engine drien pump, engine hydraulic pump 引擎液压泵EEC electronic engine control 引擎电控EFDARS expanded flight data acquisition and reporting systemEFI electronic flight instruments 电子化飞行仪表EFIS electronic flight instrument systemEGT exhaust gas temperature 排气尾温EHSI electronic horizontal situation indicator 水平状况方位指示器EICAS engine indicating and crew alerting system引擎状况警告指示ELEC electrical 与电有关的,电气科学的ELE eleation 高度;海拔EMER emergency 紧急情况ENG engage啮合,接合, engineENT entrance入口,门口, entryENTMT entertainment 娱乐EPC external power contactor 外电源接触器EPR engine pressure ratio 推力比EPRL engine pressure ratio limit 推力比范围EQUIP equipment 装备ERR error 错误ESS essential 必需品EAC eacuation 撤空;排泄物EBC engine ane and bleed control 引擎放气控制EXH exhaust 排出;排气EXT external 外部的EXTIN extinguish, extinguished 灭火器EXTING extinguishing 熄灭FF/D flight director 飞行引向器F/F fuel flow 燃油流量F/O first officerFAA Federal美国联邦 Aiation Administration行政机构FCC flight control computer 飞行控制电脑FCEU flight controls electronic unit 飞控电子单元FCU fuel control unit 燃油控制器FDR feeder 餵食器FIM Fault Isolation Manual 故障隔离手册FL flow 流量FL/CH flight leel changeFLD field(飞机)场,;(广阔的一大片)地(知识)领域;专业;(活动)范畴FLT flight (飞机的)班次FLUOR fluorescent 发亮的FMC flight management computer 飞行管理电脑FMS flight management system 飞行管理系统FREQ frequency 频率FRM Fault Reporting Manual 错误报告手册FSEU flap/slat electronic unit 副翼电控单元FT feet复, foot单英尺FWD forward 前面的GG/S glide slope, ground slope 下滑坡度GA go-around 重飞GB generator breaker 发电机断电器GCB generator circuit breaker 发电机断路器GCR generator control relay 发电机控制继电器GCU generator control unit 发电机控制组件GEN generator 发电机GHR ground handling relay 地面操作继电器GND ground 地面GP group 团体GPWS ground proximity warning system 地面接近警告GR gear 齿轮;传动装置; (飞机的)起落架GRD ground 地面GS ground speed 地速GSSR ground serice select relay 地面勤务选择继电器GSTR ground serice transfer relay 地面勤务转换继电器GW gross总量weight 总重HH/L high/low 高/低HDG heading 【航】航向HF high frequency 高频HORIZ horizontal 水平HP high pressure 高压HSI horizontal situation indicator 水平状况方位指示器HTR heater 加热器HYD hydraulic 液压的IIAS indicated airspeed 指示空速IDENT identification 识别;鉴定IDG integrated drie generatorIGN ignition 点火,发火;点火开关ILLUM illuminate, illuminated 被照明的;发光的ILS instrument landing system 仪降IMP imperial (度量衡)英制的IN in, input 输入INBD inboard 内侧的INC incorporated结合的, increase增大, increment增加INCR increase 增加IND indicator 指示器INFC interface 分界面INFLT inflight 飞行过程中的INHIB inhibit 抑制禁止INIT initiation 入门;开始实施INOP inoperatie 不活动的INPH interphone 对讲机INST instrument 仪器;仪表INT interphone 对讲机INTLK interlock 连结INTPH interphone 对讲机INTMT intermittent 时断时续的;周期性的IP intermediate pressure 中间的压力IRS inertial reference system 惯性参考系统IRU inertial惯性的reference unit 惯性参考组件ISLN isolation 隔离ISOL isolation 隔离ISI instantaneous瞬时的ertical speed indicator 垂直速度指示器MMCDP maintenance control display panel 修护控制显示面板MCP mode control panel 模式控制面板MCU modular模件concept观念 unitMDA minimum decision altitude 最小判断高度MIC microphone 扩音器;麦克风MIN minimum 最小量,最小数;最低限度MM Maintenance Manual 修护手册MOD module 组件;单元MON monitor 监视器;监控器MOT motion (机械的)装置,运转MPU magnetic pickup 检波器MSG message 信息MSTR master 主要的;总的MSU mode selector unit 模式选择组件MTG miles to go 英里MU management unit 管理组件MUX multiplexer 多路传输NN/A not applicable 可应用的NAC nacelle 引擎舱;气球吊篮NA naigation 导航NCD no computed data 无法计算资料NEG negatie 否定的; 反面的【电】负的,阴极的【数】负的NEUT neutral 中立的NLG nose landing gear 鼻轮起落架NO. number 数,数字NORM normal 正常的,正规的,标准的NRM normal 正常的,正规的,标准的NMEM RD non-olatile memory read error 故障读错误排除才能消除NMEM WR non-olatile memory write error 故障写错误排除才能消除O02 oxygen 氧气OBS obserer 观察员OK okay 对,很好地OPR operate 运转OPT option 选择权OPRN operation 操作OUT output 输出OUTBD outboard 外部的OHD oerhead 头顶(船舱)顶板OHT oerheat 过热ORD oerride 权力高於;优先於; 越过OXY oxygen 氧气PP/RST press to reset 压下清除故障P/S pitot皮托管(流速计);皮托静压管/static 静态的PA passenger address 客舱广播PASS passenger 旅客PCA power control actuator 电控致动器PCT percentage 百分比PDI pictorial deiation indicator 偏航图表示PES passenger entertainment娱乐systemPLA power leel anglePLT pilot (飞机等的)驾驶员,飞行员PMG permananet magnet generator 永磁发电机PNEU pneumatic 气动PNL panel 【电】配电盘;控电板POR point of regulation调节POS position, positie (电池的)阳极【数】正的PPOS present当前的出席的 positionPRESS pressure 压力PRG FLOW program flow error 流量程序错误PRIM primary 首要的,主要的PROC procedure 程序;手续;步骤PROG MEM ROM memory error 唯读记忆体错误PROJ projector 投射器PROT protection 保护,防护;PS pitot static 皮托管(流速计);皮托静压管PSI pounds per square inch 每平方寸上的压力磅数PSS passenger serice system 客服系统PSU passenger serice unit 客服组件PTT push to talk 发话PTU power transfer unit 动力传送组件PWR power 动力QQAD quick-attach-detach 快拆卸;使分离QTS quarts 一夸脱的容器QTY quantity 数量RR/T rate of turn 回转速率R/W MEM RAM memory error 随机存取记忆体错误R right 右边的RA radio altimeter, radio altitude 雷达高度RAT ram air turbine 冲压驱动RCR recieer 接受RDMI radio distance magnetic indicator 磁场距离指示REC recorder 记录器RECIRC recirculate 再循环REF reference 参考REFRIG refrigeration 冷冻REG regulator 调节器REL release 释放,解放REP representatie 代表性的,典型的REQ required 必须的RES resere 储备RESSTART power interrupt restart error 动力中断重新起动错误RE reerse 倒退,使倒转RF right front 右前RH right hand 右手RLSE release 释放,解放RLY relay 【电】继电器RLY/SW relay/switchRMI radio magnetic indicator 磁场方位指示RMT OUT high-speed ARINC output error 汇流排输出错误RN right noseROT rotation 旋转RPM reolutions循环,(一)周期回转,旋转per minuteRPTG reporting 报导RR right rear 後方RST reset 重新设定RTO rejected丢弃takeoff起飞RUD rudder (飞机的)方向舵RW right wing 右翼RWY runway (机场的)跑道SSAM stabilizer trim/eleator asymmetry limit module尾舵飞操组件SAT static air temperature 静压空气温度SEC second 第二次SEI standby engine indicator 紧急直接引擎指示SEL select 选择SELCAL selectie calling 飞航呼叫SER serice 服务SG signal generator 信号产生器SLCTD selected 选择SLCTR selector 选择器SO shut off ale 关断阀SP speed 速度SPD speed 速度SPD BK speed brake 速煞SQL squelch 压扁SSB single side bandSTA station 驻地(各种机构的)站,所,STAB stabilizer 安定装置;安定翼STBY standby 备用STS system status 系统状况SURF surface 表面SW switch 开关SWITCH IN switch input errorSYNC synchronous 同步的SYS system 系统SYST system 系统TT/R thrust reerser 反推力器T.O. takeoff 起飞TACH tachometer 转速计TAI thermal热的anti-iceTAS true airspeed 真空速TAT total air temperature 总温TCC turbine case cooling 涡轮(机)冷却TE trailing edge 後缘(飞机的)襟翼,阻力板TEMP temperature 温度,气温TFR transfer 转换THR thrust 推力THROT throttle 节流阀THRSH threshold 门槛THRT thrust 推力THRU through 穿过;通过遍及,在...各处;在...之间,在...之中TIE bus tie系,拴,捆,扎汇流排联系TLA thrust leer angle 推力杆角度TMC thrust management computer 推力管理电脑TMS thrust management system 推力管理系统TMSP thrust mode select panel 推力选择面板TO TO/takeoff 起飞TOL tolerance 【机】公差,容限TR transＦＯＲＭer【电】变压器 rectifier【电】整流器TRP thrust rating panel 推力等级面板TUNE tuner (频率))调整器;【无】调谐器TURB turbine 涡轮(机)TURBL turbulent, turbulence【气】湍流;(气体等的)紊流UUBR utility有多种用途的;通用的bus relay 汇流排继电器UPR upperUSB upper side band 【机】传送带 (无线电的)波段,频带/NA ertical naigation 【经】纵向联合的导航/S ertical speed 垂直的速率ERT ertical 垂直的ERT SPD ertical speed 垂直的速率FY erify 验证G ertical gyro 垂直回转仪罗盘HF ery high frequency 超高频无线电IB ibration 震动LD alid 合法的;有效的L ale 【机】阀,活门OL olume 量;额OLT oltage 电压;伏特数OR HF omni range receier 方向无线识标OX oice 声音TR ideo tape reproducer (录音,录影的)播放装置WW/D wiring线路diagram图解W/W wheel well 轮舱WARN warning 警告;警报WG wing 机翼WHL wheel 轮子 ; 变换方向WHLS wheels 车轮WPT waypoint 位子点WSHLD windshield 挡风玻璃WX weather 天气WXR weather 气象雷达XX-CH cross channel 交叉频道X-CHAN cross channel 交叉频道XDCR transducer 变换器XMISSION transmission 传送XMIT transmit 发射XMTR transmitter 发射机XPNDR transponder 询答机YY/D yaw damper 阻尼器。
飞机系统5飞机燃油系统
5 飞机燃油系统
本章介绍的飞机燃油系统，指从燃油箱到发动机驱动泵之 间的供油管路系统。
功用：储存燃油，按规定的压力向发动机输送一定流量的 洁净燃油，满足发动机各工作状态的要求。 ? 作为冷源冷却滑油和液压油等 ? 调整飞机重心及平衡-燃油负荷是飞机重量的重要部分， 燃油负载的变化对飞行控制有重要的影响
抽吸供油： 在主油箱所有增压泵都失效时，发动机驱 动的燃油泵通过旁通活门将油抽吸到发动 机。中央油箱无旁通活门（两泵失效时不 可用，重新计算航时）
5.1.2油箱通气系统
防止加油时油箱内产生过大的正压； 在飞行中给油面提供冲压空气压力，防止因耗油 产生负压，保证顺利加油和向发动机供油； 排出燃油蒸气，防止形成爆炸条件。
An aviation fuel truck
underground fuel pipes
⑤放油的注意事项
? 飞机空中放油的目的是防止 超重着陆，或降低带故障着 陆起火的可能性。
? 为防止污染和着火，放油应 在指定的空域和指定的高度。
? 注意留够余油，一般达到最 大着陆重量为宜。
? 飞机应处于净外形状态
? 涡轮发动机 使用煤油，叫 航空煤油jet fuel or kerosene
Aviation fuel types, grades, and colors
low-lead100-octane, or 100LL
油箱口标识——牌号和油量单位
④重力加油防污染
小型飞机 机翼上 表面加油口。加油 前清洁，每次加油 后飞行员要确保油 箱盖盖好
飞机燃油系统的基本组成
? 控制活门
– 交输活门
? 正常供油时关断，交输供油时打开。
737-300FUEL SYS
飞机部件英语翻译对照
1 飞机及其主要部件 AIRCRAFT AND MAIN COMPONENTS飞机 aircraft, airplane1.1飞机类型 AIRCRAFT TYPE民用飞机 civil aircraft干线机 trunk aircraft, trunkliners支线机 regional aircraft, commuter商用飞机 commercial aircraft客货两用机 combination aircraft旅客机 passenger aircraft运输机 transport aircraft宽体飞机 wide fuselage aircraft窄机身飞机 narrow-bodied aircraft大型运输机 large transport aircraft货机 cargo aircraft, airfreighter, freight aircraft公务机/行政勤务飞机 business/executive aircraft, administrative aircraft 公务喷气机 business jet aircraft, corporate jet aircraft通用飞机 general-purpose aircraft私人飞机 private owner airplane适航飞机 airworthy aircraft全天候飞机 all-weather aircraft后掠翼飞机 swept back wing airplane喷气式飞机 jet airplane燃气涡轮式飞机 turbine-engine aircraft涡轮风扇式飞机 turbofan aircraft涡轮喷气式飞机 turbojet airplane 双喷气发动机飞机 twin-jet aircraft 亚音速飞机 subsonic aircraft 中程飞机 medium-range aircraft 中短程飞机 short/medium aircraft 远程飞机 long-distance aircraft 半硬壳式飞机 semimonocoque aircraft 前（后）三点飞机 aircraft with nose (tail) wheel 原型机,样机 prototype aircraft, mockup 试验型飞机 development aircraft 基本型飞机 basic aircraft 改型飞机 modified aircraft 批生产飞机mass-produced aircraft1.2 飞机主要部件及其结构AIRCRAFT MAIN COMPONENTS AND STRUCTURAL MEMBERS1.2.1 机身 FUSELAGE机体 airframe, body 机头 nose 机身 fuselage 前机身 forward fuselage 中机身 mid fuselage 中后机身 mid-aft fuselage 后机身 aft fuselage 机身下部 lower fuselage 机身中上部 mid-upper fuselage 机身上部 upper fuselage 增压机身 pressurized fuselage 机身结构 fuselage structure 机体结构 airframe structure 半硬壳式机身 semimonocoque fuselage 半硬壳式结构 semimonocoque structure 主要结构primary structure次要结构，辅助结构 secondary structure,auxiliary structure 基本结构 basic structure复合材料结构 composite material structure 胶结蜂窝结构 honeycomb bonded structure金属胶结结构 metal-to-metal adhesive bonded structure 加强结构 reinforced structure 梁肋结构 spar-and rib structure 机身蒙皮 fuselage skin隔框 bulkhead (BHD), frame 机身隔框 fuselage frame 圆形隔框circumferential frame 机身与机翼对接隔框 fuselage-wing frame 翼梁固定隔框 spar frame 前梁固定隔框 front spar frame 后梁固定隔框 rear spar frame 气密隔框 pressure bulkhead 防火隔板（墙） fire bulkhead 机身桁梁（大梁） longeron 横梁 transverse beam 纵梁 longitudinal beam 长桁 stringer,longeron 角形桁条 angle stringer “Z”型桁条 "Z"section stringer “Π”型桁条"hat-section" stringer加强桁条 heavy stringer 龙骨梁 keel beam 龙骨 keel 地板 floor panel 地板梁 floor beam 座椅滑轨 seat track 气密地板pressure floor 整流片（带，包皮）fillet机身机翼接合整流带（翼根整流带） fuselage-to-wing fillet, wing-root fillet 整流罩 fairing机身整流罩 fuselage fairing机身机翼整流罩 fuselage-to-fairing雷达天线罩 radome天线整流罩 antenna fairing搭接板 splice机身搭接板 fuselage splice纵向搭接板 longitudinal splice长桁搭接板 stringer splice加强板（双搭接板） double splice机身站位 station (STA) 站位线 station line机身横截面 fuselage cross section水平线 water line (WL)纵剖线(横向站位线） buttock line （BL）中心线 center line （CL）机身气密包线 fuselage pressure envelope分离面 break工艺分离面 production break, manufacturing break主舱地板 main deck 货舱地板 cargo deck驾驶舱地板 flight compartment floor纵向加强件 intercostal转折梁 crease beam尾锥 tailcone化纤蒙皮 chemical-milled skin 1.2.2机翼 WING ·机翼类型 WING TYPE基本翼 basic wing 中央翼 center wing 中外翼（翼）inboard wing外翼 outboard wing 翼尖 wing tip上单翼 upper-monowing 下单翼 lower-monowing上反角机翼 anhedral wing, positive dihedral wing 下反角机翼 negative dihedral wing 带盒形梁的机翼 box-spar wing 双梁式机翼 double-spar wing 整体油箱机翼 fuel-tight wing 有襟翼的机翼 flapped wing 后掠机翼 sweptback wing 前缘开缝机翼 nose-slot wing 翼梢小翼 winglets·机翼主要结构 PRIMARY WING STRUCTURE 前缘 leading edge 后缘 trailing edge 翼尖整流罩 wing-tip fairing 翼根整流带 wing-root fillet 翼根整流罩 wing-root fairing 翼梁 wing spar 盒形翼梁 box spar 前梁 front spar 后梁 rear spar 纵墙（假梁） false spar 副翼翼梁 aileron spar辅助梁 secondary spar, auxiliary spar 展向梁 spanwise beam腹板式翼梁 plated-web spar, web-type spar 整体式翼梁 one-piece spar 后缘翼梁 trailing edge beam起落架支撑梁landing gear (support) beam 机翼辅助梁（机翼纵墙） wing web （W/W） beam 翼盒 wing box 中央翼盒 center wing box 扭力盒 torsion box 机翼整体油箱 integral fuel tank 翼肋 wing rib 油箱端肋 tank end rib 加强肋 reinforced rib梁间加强肋intercostal,reinforced rib整体肋 one-piece rib 腹板 web 缘条 chord,flange 支柱，加强件 stiffener 长桁 stringer上长桁 upper stringer ER 下长桁 lower stringer 机翼蒙皮 wing skin 蒙皮壁板 skin panel 铝合金蒙皮 alumium skin 蜂窝结构蒙皮 honeycomb skin 双层蒙皮 double skin 轻合金蒙皮 light-alloy skin 抗拉蒙皮 tension skin 加强蒙皮 reinforced skin 蒙皮 inner skin 外蒙皮 outer skin 上蒙皮 upper skin 下蒙皮 lower skin 翼剖面（翼型） airfoil襟翼滑轨整流罩 flap track fairing 根部（三叉）接头 terminal fitting ·襟翼 WING FLAP 侧襟翼 inboard flaps 外侧襟翼 outer flaps 前缘襟翼 leading-edge flap 后缘襟翼 trailing-edge flap襟翼滑轨安装接头 flap track attachment fitting ·缝翼 SLAT前缘缝翼 leading-edge slat 可操纵缝翼 movable slat ·副翼 AILERON 扰流板 spoiler 减速板 airbrake 减升板 lift dumper 调整片 tab, adjustable tab 副翼调整片 aileron trim tab 铰头 hinge fitting 作动器接头 actuator fitting 1.2.3 尾翼TAIL, EMPENNAGE安定面 STABILIZER水平安定面 horizontal stabilizer水平尾翼 horizontal tail垂直安定面 vertical stabilizer垂直尾翼 vertical tail,vertical fin全动垂直尾翼 all-movable vertical tail,all-movable fin操纵面，舵面 control surface舵面锁 gust lock, control lock方向舵 rudder升降舵 elevator背鳍 dorsal fin翼尖 wing tip补偿装置 COMPENSATOR迎角补偿器 angle-of-attack compensator配平装置 trimmer调整片 trim tab, adjustable tab升降舵调整片 elevator trim tab方向舵调整片 rudder trim tab固定调整片 fixed trim tab操纵调整片 control tab方向舵操纵装置 rudder control unit偏航阻尼器 yaw damper安定面结构 STABILIZER STRUCTURE前缘 leading edge (LE) 固定前缘 fixed leading edge 可卸前缘 removable leading edge 前梁 front spar 后梁 rear spar 扭力盒 torque box 长桁 stringer 肋rib安定面配平致动螺杆 stabilizer trim jack screw配重 balance weight, counter balance, mass balance 整体壁板 intergral panel 中梁 middle spar 中央盒板 center section 外伸段 outer section 1.2.4 舱门 DOORS ·舱门 DOORS 登机门entry door旅客门 passenger door 旅客登机门 passenger entry door 驾驶舱门 crew door 货舱门 cargo door行舱门 baggage door, luggage door 应急门（出口） emergency door (exit) 服务舱门 service door 检修门 access door 厨房门 galley door 盥洗室门 lavatory door 登机梯门 airstair door 电气设备舱门 electrical door 电子设备舱门 electronics door 起落架舱门 landing gear door驾驶舱应急出口 escape hatch, overhead hatch 辅助动力装置舱门 APU(Auxiliary Power Unit) access door 电子/电气舱门 E&E compartment door 冲压空气涡轮舱门 RAT compartment door 前起落架舱门 nose landing gear door 主起落架舱门 main landing gear door ·门结构 DOOR STRUCTURE 门框 door frame, door-case 门梁 door beam 门加强肋 door stiffening rib 门上/下托架 upper/lower carriage 门的衬板 door lining 门槛 doorsill门操纵机构 door control mechanism(door operation mechanism) 手操纵 manual control 电操纵 electrical control 门手柄 door handle 门把手 door-knob 辅助手柄 assist handle 应急手柄 emergency handle 应急起动手柄 emergency trigger lever 选择手柄 selector lever 门锁 door lock 门锁闩 door latch 锁闩杆 latch rod 锁闩滚轮latch rolle门操纵杆 door control rod 门扭力管（管轴） door torque tube锁稍lock pin, latch pin, catch pin 门锁定装置（闸柄） trigger门锁杆机构 girt bar mechanism 开锁杆 open lock release rod (锁杆)啮合 engagement (锁杆)分离 detachment 手摇把 crank 推拉杆 push-pull rod 凸轮板 cam plate锁住曲柄滚轮 latching crank roller 开关曲柄推杆 cocking crank pushrod 门导轨 door track 门导轨小齿轮 door track pinion 门导轨齿条 door track rack 导轨导向滚轮 track guide roller 导向臂 guide arm 导向稍 guide pin 导向凸轮 guide cam 凸轮导轨 cam track 凸轮轴 camshaft 凸轮随动装置 cam follower摇臂 bellcrank, rocker铰链臂 hinge arm半径连杆 radius link门作动器 actuator作动器离合器 actuator clutch齿轮箱 gearbox齿条齿轮传动 rack and pinion drive角传动装置 angle drive软轴 flex shaft横传动轴 cross drive shaft门止动块 door stop门止动块接头 door stop fitting卡爪 pawl门打开定位卡销 door open detent偏心弹簧卡销 overcenter spring detent偏心衬套 eccentric bushing齿形板 serrated plate轴钩 pivot hook后部垫块 heel pad安装支架 support bracket, mounting bracket防磨板 wear plate抗剪销 shear pin门警告系统 door warning system门传感器 door sensor锁闩传感器 latch sensor门锁开关 door lock switch门位置开关 door position switch门速度限制器 door speed limiter平衡器 counterbalance减震器，缓冲器 snubber应急撤离系统 emergency evacuation system单通道撤离滑梯 single channel evacuation slide 滑梯充气瓶 slide inflation cylinder抽气管（器） aspirator护罩 shroud滑梯包装板 pack board喷射器带条 ejector strap释放钢索 release cable滑梯收进装置 slide retractor触点接头 stop fitting1.2.5 窗 WINDOWS驾驶舱窗 flight compartment (deck) windows旅客舱窗 passenger compartment (cabin) windows旅客登机门窗 passenger entry door windows服务门窗 service door windows检查/观察窗 inspection/observation windows双层玻璃窗 double-glazed window电热防冰窗 electrically antiiced window加温玻璃窗 heated windows客舱舷窗 cabin window机头窗 nose window, forward-view window后视窗 rear-view window固定客舱舷窗 fixed cabin windows滑动窗 sliding windows风挡 windshield防鸟撞风挡 withstand bird impact windshield, bird-proof windshield 防弹玻璃风挡 armor glass windshield电阻丝加热风挡 electrically heated windshield热气加温风挡 hot-air windshield双层玻璃风挡 twin-pane windshield三层风挡 tri-layer windshield多层风挡 laminated windshield金膜风挡玻璃 gold film windshield窗玻璃 windowpane强化玻璃 tempered glass外层薄强化玻璃层 outer thin-tempered glass layer 中间隔层 interlayer丙烯酸有机玻璃 arcylic glass导电涂层 conductive coating层玻璃 inner pane中层玻璃 middle pane外层玻璃 outer pane风挡雨刷 windshield wiper风挡的安装 windshield installation风挡框 windshield frame窗槛 windowsill窗帘 window curtain, curtain安装环 mounting ring丙烯酸垫圈 acrylic spacer橡胶模压密封件 rubber molded seal气动校平器 aerodynamic smoother窗加热控制 window heat control汇流条 bus bar汇流条接头 bus bar terminal电源接头 power terminal温度控制传感器 temperature control sensor温度调节器 heat controller加热元件 heating elements加温模块 heat module过热开关 overheat switch过热温度自动调节器 overheat thermostat过热指示灯 overheat indicator light备用传感器 spare sensor旅客舱窗的安装 passenger cabin window installation 窗固定接头 window retainer fitting锯齿形板 serrated plate弹簧卡子 spring clip密封隔板 seal diaphragm放密封隔板槽口 diaphragm notch密封垫环 seal spacer ring支承卡子 backup clip窗框半边槽 reveal通气孔 vent hole窗周缘密封件 peripheral seal防磨涂层 anti-fretting coating检查和观察设备 inspection and observation equipment 货舱观察窗 cargo compartment viewer宽角度观察窗 wide angle viewer1.2.6 短舱/吊挂 NACELLE/PYLON ·类型 TYPE发动机短舱 engine nacelle涡轮喷气发动机短舱 turbo-jet engine nacelle涡轮风扇发动机短舱 turbofan engine nacelle后机身发动机短舱 aft fuselage mounted engine nacelle 可卸短舱 removable nacelle ·结构 STRUCTURE进气道 air inlet风扇段舱门 fan cowl door反推力装置 thrust reverser吊挂前缘整流罩 pylon leading-edge fairing吊挂后缘整流罩 pylon trailing-edge fairing吊挂前梁 pylon front spar吊挂后梁 pylon rear spar封闭肋 closing rib辅助梁 auxiliary spar主承力结构 main frame防火墙 fire wall肋 rib整流罩 fairing腹板 web拼接板 splice plate连接条（片） connection strap加强板 doubler。
飞机燃油系统图解(英文原版)
14-1Basic Fuel System RequirementsAll powered aircraft require fuel on board to operate the engine(s). A fuel system consisting of storage tanks, pumps, filters, valves, fuel lines, metering devices, and monitoring devices is designed and certified under strict Title 14 of the Code of Federal Regulations (14 CFR) guidelines. Each system must provide an uninterrupted flow of contaminant-free fuel regardless of the aircraft’s attitude. Since fuel load can be a significant portion of the aircraft’s weight, a sufficiently strong airframe must be designed. Varying fuel loads and shifts in weight during maneuvers must not negatively affect control of the aircraft in flight.Aircraft Fuel SystemChapter 1414-2Figure 14-1. Aircraft fuel systems must deliver fuel during any maneuver for which the aircraft is certified.Each Federal Aviation Administration (FAA) certified aircraft is designed and constructed under FARs applicable to that type of aircraft. The certification airworthiness standards are found in 14 CFR as follows: 14 Part 23—Normal, Utility, Acrobatic, and Commuter Category Airplanes 14 Part 25—Transport Category Airplanes 14 Part 27—Normal Category Rotorcraft14 Part 29—Transport Category Rotorcraft14 Part 31—Manned Free Balloons Additional information is found in 14 CFR part 33. It addresses airworthiness standards for engines and pertains mainly to engine fuel filter and intake requirements.Under each 14 CFR part for a specific aircraft to be certified,paragraphs 951 through 1001 address very specific design criteria required to ensure the fuel system functions properly. These paragraphs from 14 CFR part 23, Normal, Utility, Acrobatic, and Commuter Category Airplanes, are summarized below. Airworthiness standards specified for air carrier and helicopter certification are similar. Although the technician is rarely involved with designing fuel systems, a review of these criteria gives insight into how an aircraft fuel system operates. Each fuel system must be constructed and arranged to ensure fuel flow at a rate and pressure established for proper engine and auxiliary power unit (APU) functioning under each likelyoperating condition. This includes any maneuver for which certification is requested and during which the engine or APU may be in operation. [Figure 14-1] Each fuel system must be arranged so that no fuel pump can draw fuel from more than one tank at a time. There must also be a means to prevent the introduction of air into the system.Each fuel system for a turbine engine powered airplane must meet applicable fuel venting requirements. 14 CFR part 34 outlines requirements that fall under the jurisdictionof the Environmental Protection Agency (EPA). A turbine engine fuel system must be capable of sustained operation throughout its flow and pressure range even though the fuel has some water in it. The standard is that the engine continues to run using fuel initially saturated with water at 80 °F having 0.75 cubic centimeters (cm) of free water per gallon added to it and then cooled to the most critical condition for icing likely to be encountered in operation.Fuel System IndependenceEach fuel system for a multiengine airplane must be arrangedso that, in at least one system configuration, the failure of anyone component (other than a fuel tank) does not result in the loss of power of more than one engine or require immediate action by the pilot to prevent the loss of power of more thanone engine.If a single fuel tank (or series of fuel tanks interconnected to function as a single fuel tank) is used on a multiengine airplane, independent tank outlets for each engine, each incorporating a shut-off valve at the tank, must be provided. The shutoff valves may serve as firewall shutoff valves, which are also required. However, note that if the line between the valve and the engine compartment contains more than one quart of fuel (or any greater amount shown to be safe) that can escape into the engine compartment, an additionalfirewall shutoff valve is needed. Lines and any componentsfrom each tank outlet to each engine must be completely independent of each other.The fuel tank must have at least two vents arranged to minimize the probability of both vents becoming obstructed simultaneously. The filler caps must be designed to minimize the probability of incorrect installation or in-flight loss. Fuel System Lightning ProtectionThe fuel system must be designed and arranged to prevent the ignition of fuel vapor within the system by direct lightning strikes or swept lightning strokes (where highly probable). Swept strokes occur when the lightning strike is deformed by interaction with aerodynamic forces and propagates in a unique manner due to the material and shape of the airframe surfaces. Corona and streamering must also be inhibited at fuel vent outlets since they may ignite the fuel-air mixture. A corona is a luminous discharge that occurs as a result of an electrical potential difference between the aircraft and the surrounding area. Streameringis a branch-like ionized path that occurs in the presence of a direct stroke or under conditions when lightning strokes areimminent. [Figure 14-2]14-3Figure 14-2. Lightning streamering at the wingtips of a jet fighter.Fuel FlowThe ability of the fuel system to provide fuel at a rate of flow and pressure sufficient for proper engine operation is vital in aircraft. Moreover, the fuel system must deliver the fuel at the aircraft attitude that is most critical with respect to fuel feed and quantity of unusable fuel. Tests are performed todemonstrate this performance. Fuel flowmeters are installed on most aircraft. During testing, the flowmeter is blocked and fuel must flow through or bypass the meter and still supply the engine at sufficient rate and pressure.For gravity-flow fuel systems, the fuel flow rate must be 150 percent of the takeoff fuel consumption of the engine. For fuel pump systems, the fuel flow rate for each pump system (main and reserve supply) for each reciprocating engine must be 125 percent of the fuel flow required by the engine at the maximum takeoff power. However, the fuel pressure, with main and emergency pumps operating simultaneously, must not exceedthe fuel inlet pressure limits of the engine. Auxiliary fuel systems and fuel transfer systems may operate under slightlydifferent parameters. Turbine engine fuel systems mustprovide at least 100 percent required by the engine undereach intended operating condition and maneuver.On aircraft with multiple fuel tanks, performance ismonitored when switching to a new tank once fuel has beendepleted from a tank. For reciprocating, naturally aspirated,single-engine aircraft in level flight, 75 percent maximum continuous power must be obtainable in not more than 10 seconds. For turbocharged aircraft, 20 seconds is allowed. Twenty seconds is also allowed on multiengine aircraft.Flow Between Interconnected TanksIn a gravity feed fuel system with interconnected tank outlets, it must be impossible for enough fuel to flow between the tanks to cause an overflow of fuel from any tank vent under the conditions in 14 CFR part 23, section 23.959. If fuel can be pumped from one tank to another in flight, the fuel tank vents and the fuel transfer system must be designed so that no structural damage to any airplane component can occur because of overfilling of any tank.Unusable Fuel SupplyThe unusable fuel supply for each tank must be established. It cannot be less than that quantity at which the first evidence of malfunctioning appears under the most adverse fuel feed condition occurring under each intended operation and flight maneuver involving that tank. The effect on the usable fuel quantity as a result of a failure of any pump is also determined.Fuel System Hot Weather OperationEach fuel system must be free from vapor lock when using fuel at its critical temperature, with respect to vapor formation, when operating the airplane in all critical operating and environmental conditions for which approval is requested. For turbine fuel, the critical temperature must be 110 °F, −0°, +5 °F or the maximum outside air temperature for which approval is requested, whichever is more critical.Fuel TanksEach fuel tank must be able to withstand, without failure, the vibration, inertia, fluid, and structural loads to which it may be subjected in operation. Fuel tanks with flexible linersmust demonstrate that the liner is suitable for the particularapplication. The total usable capacity of any tank(s) must be enough for at least 30 minutes of operation at maximum continuous power. Each integral fuel tank must have adequate facilities for interior inspection and repair. Additionally, each fuel quantity indicator must be adjusted to account for the unusable fuel supply. Fuel Tank Tests Aircraft fuel tanks must be able to withstand the forces thatare encountered throughout the entire spectrum of operation.Various tank testing standards exist. A main focus is to ensurethat tanks are strong enough to remain fully operational and not deform when under various loads. Vibration resistancewithout leaking is also a concern. Tanks are tested under themost critical condition that may be encountered. Fuel tank14-4Figure 14-3. Aircraft fuel tanks must be designed to retain fuel inthe event of a gear-up landing. The fuel system drain valve should be located to prevent spillage.supporting structure must be designed for the critical loads that could occur during flight or when landing with fuel pressure loads.Fuel Tank Installation Various standards exist for fuel tank installations. No fuel tank may be on the engine side of a firewall, and there must be at least ½-inch of clearance between the fuel tank and the firewall. Each tank must be isolated from personnel compartments of the aircraft by a fume-proof and fuel-proof enclosure that is vented and drained to the exterior of theairplane. Pressurization loads should not affect the tank(s). Each tank compartment must be ventilated and drained to prevent the accumulation of flammable fluids or vapors. Compartments adjacent to tanks must also be ventilated and drained.Aircraft fuel tanks must be designed, located, and installed to retain fuel when subjected to inertia loads resulting from ultimate static load factors, and under conditions likely to occur when the airplane lands on a paved runway at a normal landing speed with the landing gear retracted. They must also retain fuel if one of the gear collapses or if an engine mount tears away. [Figure 14-3]Many aircraft have fuel tanks that are not metal. Bladder fuel tanks have their own standards of construction and installation. As with metal tanks, there must be pads to prevent any chafing between each tank and its supports. The padding must be nonabsorbent or treated to prevent the absorption of fuel. Bladders must be supported so they are not required to support the entire fuel load. Surfaces adjacent to the liner must be smooth and free from projections that could cause wear. A positive pressure must be maintained within the vapor space of each bladder cell under any condition of operation, or it should be shown not to collapse under zero or negative pressure. Siphoning of fuel or collapse of bladder fuel cells should not result from improper securing or loss of the fuel filler cap. Bladder-type fuel cells must have a retaining shell at least equivalent to a metal fuel tank in structural integrity.Fuel Tank Expansion SpaceEach fuel tank must have an expansion space of not less than two percent of the tank capacity. This is waved if the tank vent discharges clear of the airplane, in which case no expansion space is required. It must be impossible to fill the expansion space inadvertently with the airplane in the normal ground attitude.Fuel Tank SumpKeeping contaminants out of the fuel delivered to the engine begins with the proper construction and installation of the fuel tank(s). Each tank must have a drainable sump with an effective capacity, in the normal ground and flightattitudes, of 0.25 percent of the tank capacity, or 1/16 gallon,whichever is greater. Each fuel tank must allow drainage of any hazardous quantity of water from any part of the tank to its sump with the airplane in the normal ground attitude. Reciprocating engine fuel systems must have a sediment bowl or chamber that is accessible for drainage. Its capacity must be 1 ounce for every 20 gallons of fuel on board. Each fuel tank outlet must be located so that water drains from allparts of the tank, except the sump, to the sediment bowl or chamber in the normal flight attitude.Fuel Tank Filler ConnectionEach fuel tank filler connection must be specifically marked. Aircraft with engines that use only gasoline fuel must have filler openings no larger than 2.36 inches in diameter. Turbine fuel aircraft filler openings must be no smaller than 2.95 inches. Spilled fuel must not enter the fuel tank compartment or any part of the airplane other than the tank itself. Each filler cap must provide a fuel-tight seal for the main filler opening. However, there may be small openings in the fuel tank cap for venting purposes or for the purpose of allowing passage of a fuel gauge through the cap. Fuel filling points must have a provision for electrically bonding the airplane to ground fueling equipment (except pressure fueling connection points).Fuel Tank Vents and Carburetor Vapor VentsTo allow proper fuel flow, each fuel tank must be vented from the top part of the expansion space. Vent outlets must be located and constructed in a manner that minimizes the possibility of being obstructed by ice or other foreign matter. Siphoning of fuel during normal operation must not occur. Venting capacity must allow the rapid relief of excessive differences of pressure between the interior and exterior of the tank. The airspaces of tanks with interconnected outlets must also be interconnected. There must be no point in any vent line where moisture can accumulate either on theground or during level flight (unless drainage is provided by an accessible drain valve).Fuel tank vents may not terminate at a point where the discharge of fuel from the vent outlet constitutes a fire hazard or from which fumes may enter personnel compartments. The vents must be arranged to prevent the loss of fuel when the airplane is parked in any direction on a ramp having a one-percent slope. Fuel discharged because of thermal expansion is allowed.Each carburetor with vapor elimination connections and each fuel injection engine employing vapor return provisions must have a separate vent line to lead vapors back to the top of one of the fuel tanks. If there is more than one tank and it is necessary to use these tanks in a definite sequence for any reason, the vapor vent line must lead back to the fuel tank to be used first, unless the relative capacities of the tanks are such that return to another tank is preferable.For acrobatic category airplanes, excessive loss of fuel during acrobatic maneuvers, including short periods of inverted flight, must be prevented. It must be impossible for fuel to siphon from the vent when normal flight has been resumed after any acrobatic maneuver for which certification is requested.Fuel Tank OutletThere must be a fuel strainer for the fuel tank outlet or for the booster pump. On reciprocating-engine aircraft, the strainer must have 8 to 16 meshes per inch. The clear area of each fuel tank outlet strainer must be at least five times the area of the outlet line and the strainer diameter must be at least that of the fuel tank outlet. It must also be accessible for inspection and cleaning. Turbine-engine aircraft fuel strainers must prevent the passage of any object that could restrict fuel flow or damage any fuel system component.Pressure Fueling SystemsPressure fueling systems are used on many large, high-performance, and air carrier aircraft. Each pressure fueling system fuel manifold connection must have means to prevent the escape of hazardous quantities of fuel from the system if the fuel entry valve fails. A means for automatic shutoff must be provided to prevent the quantity of fuel in each tank from exceeding the maximum quantity approved for that tank. A means must also be provided to prevent damage to the fuel system in the event of failure of the automatic shutoff means prescribed in this section. All parts of the fuel system up to the tank that are subjected to fueling pressures must have a proof pressure of 1.33 times and an ultimate pressure of at least 2.0 times the surge pressure likely to occur during fueling.Fuel PumpsFuel pumps are part of most aircraft fuel systems. Standards exist for main pumps and emergency pumps. Operation of any fuel pump may not affect engine operation by creating a hazard, regardless of the engine power or thrust setting or the functional status of any other fuel pump. On reciprocating engines, one main fuel pump must be engine-driven and there must be at least one for each engine. Turbine engines also require dedicated fuel pumps for each engine. Any pump required for operation is considered a main fuel pump. The power supply for the main pump for each engine must be independent of the power supply for each main pump for any other engine. There must also be a bypass feature for each positive displacement pump.Emergency pumps are used and must be immediately available to supply fuel to the engine if any main pump fails. The power supply for each emergency pump must be independent of the power supply for each corresponding main pump. If both the main fuel pump and the emergency pump operate continuously, there must be a means to indicate a malfunction of either pump to the appropriate flight crew member. Fuel System Lines and FittingsEven aircraft fuel system fluid lines and fittings have standards to ensure proper fuel system operation. Each fuel line must be installed and supported to prevent excessive vibration and to withstand loads due to fuel pressure and accelerated flight conditions. Lines connected to components of the airplane, between which relative motion could exist, must have provisions for flexibility. Flexible hose assemblies are used when lines may be under pressure and subject to axial loads. Any hose that is used must be shown to be suitable for a particular application. Where high temperatures may exist during engine operation or after shutdown, fuel hoses must be capable of withstanding these temperatures.Fuel System ComponentsFuel system components in an engine nacelle or in the fuselage must be protected from damage that could result in spillage of enough fuel to constitute a fire hazard as a result of a wheels-up landing on a paved runway.Fuel Valves and ControlsThere must be a means to allow appropriate flight crew members to rapidly shut off the fuel to each engine individually in flight. No shutoff valve may be on the engine side of any firewall. There must be means to guard against inadvertent operation of each shutoff valve and means to reopen each valve rapidly after it has been closed. Each valve and fuel system control must be supported so that loads resulting from its operation, or from accelerated flight14-514-6VALVEON VALVEON FAULT Figure 14-4. The fuel jettison panel on a Boeing 767.Figure 14-5. Fuel being jettisoned free of the airframe on a transportcategory aircraft .conditions, are not transmitted to the lines connected to the valve. Gravity and vibration should not affect the selected position of any valve.Fuel valve handles and their connections to valve mechanisms must have design features that minimize the possibility of incorrect installation. Check valves must be constructed to preclude incorrect assembly or connection of the valve. Fuel tank selector valves must require a separate and distinct action to place the selector in the OFF position. The tank selector positions must be located in such a manner that it is impossible for the selector to pass through the OFF position when changing from one tank to another.Fuel Strainer or FilterIn addition to fuel tank strainers already discussed, there must be a fuel strainer, or filter, between the fuel tank outlet and the inlet of either the fuel metering device or an engine-driven positive displacement pump, whichever is nearer the fuel tank outlet. This fuel strainer, or filter, must be accessible for draining and cleaning and must incorporate a screen or element that is easily removable. The fuel strainer should have a sediment trap and drain, except that it need not have a drain if the strainer or filter is easily removable for drain purposes. The fuel strainer should also be mounted so that its weight is not supported by the connecting lines. It should have the capacity to ensure that engine fuel system function is not impaired when fuel is contaminated to a degree that is greater than that established for the engine during its type certification. Commuter category airplanes must have a means to automatically maintain the fuel flow if ice clogs a filter.Fuel System DrainsAircraft fuel systems must be fitted with at least one drain to allow safe drainage of the entire fuel system with the airplane in its normal ground attitude. The drain must discharge the fuel clear of all parts of the aircraft. A readily accessible drain valve that can easily be opened and closed is required. It must have a manual or automatic means for locking in the closed position, and it must be observable that it is closed. Fuel should be collectible from the system drain valve so it can be examined. The location of the valve should be such that spillage is prevented should a gear up landing be made. Fuel Jettisoning SystemIf an aircraft’s design landing weight is less than that of the maximum takeoff weight, a situation could occur in which a landing is desired before sufficient fuel has burned off to lighten the aircraft. Fuel jettisoning systems are required on these aircraft so that fuel can be jettisoned in flight to avoid structural damage cause by landing the aircraft when it is too heavy. Fuel jettisoning systems are also referred to as fuel dump systems. [Figure 14-4] Fuel jettisoning systems must meet several standards. The average rate of fuel jettisoning must be at least 1 percent of the maximum weight per minute, except that the time required to jettison the fuel need not be less than 10 minutes. Fuel jettisoning must be demonstrated at maximum weight with flaps and landing gear up and in a power-off glide at 1.4 VS 1. It must also be demonstrated during a climb with a critical engine inoperative and the remaining engines at maximum continuous power. Finally, the fuel jettisoning system must be performed during level flight at 1.4 VS 1 if the glide and climb tests show that this condition could be critical.During the demonstration of the fuel jettisoning system, it must demonstrate that it operates without fire hazard. No fuel or fumes can enter any part of the aircraft. The fuel must discharge clear of any part of the aircraft and the jettisoning operation must not adversely affect the controllability of the airplane. [Figure 14-5] The system must be designed so that any reasonably probable single malfunction in the system does not result in a hazardous condition due to unsymmetrical jettisoning of, or inability to jettison, fuel. The fuel jettisoning valve must be designed to allow flight crewmembers to close the valve during any part of the jettisoning operation.On reciprocating-engine aircraft, the jettisoning system must be designed so that it is not possible to jettison the fuel in the tanks used for takeoff and landing below the level allowing 45 minutes of flight at 75 percent maximum continuous power. However, if there is an auxiliary control independent of the main jettisoning control, the system may be designed to jettison all the fuel. For turbine engine powered airplanes, the jettisoning system must be designed so that it is not possible to jettison fuel from the tanks used for takeoff and landing below the fuel level that would allow climb from sea level to 10,000 feet plus 45 minutes cruise at a speed for maximum range. If certain flight control configurations negatively affect jettisoning the fuel, a placard stating so must be posted next to the actuation control in the cockpit.Types of Aviation FuelEach aircraft engine is designed to burn a certain fuel. Use only the fuel specified by the manufacturer. Mixing fuels is not permitted. There are two basic types of fuel discussed in this section: reciprocating-engine fuel (also known as gasoline or AVGAS) and turbine-engine fuel (also known as jet fuel or kerosene).Reciprocating Engine Fuel—AVGAS Reciprocating engines burn gasoline, also known as AVGAS. It is specially formulated for use in aircraft engines. Combustion releases energy in the fuel, which is converted into the mechanical motion of the engine. AVGAS of any variety is primarily a hydrocarbon compound refined from crude oil by fractional distillation. Aviation gasoline is different from the fuel refined for use in turbine-powered aircraft. AVGAS is very volatile and extremely flammable, with a low flash point. Turbine fuel is a kerosene-type fuel with a much higher flash point so it is less flammable. Aircraft engines must perform throughout a wide range of demanding conditions. They must be lightweight and produce significant power in a wide range of atmospheric and engine operating temperatures. The gasoline used must support uninterrupted combustion throughout this range and must truly burn rather than explode or detonate. This ensures maximum power derivation and minimal engine wear. Over the years, AVGAS has been available in different formulas. These mostly correlate to how much energy can be produced without the fuel detonating. Larger, high-compression engines require fuel with a greater amount of potential power production without detonation than smaller low-compression engines.VolatilityOne of the most important characteristics of an aircraft fuel is its volatility. Volatility is a term used to describe how readily a substance changes from liquid into a vapor. For reciprocating engines, highly volatile fuel is desired. Liquid gasoline delivered to the engine induction system carburetor must vaporize in the carburetor to burn in the engine. Fuel with low volatility vaporizes slowly. This can cause hard engine starting, slow warm-up, and poor acceleration. It can also cause uneven fuel distribution to the cylinders and excessive dilution of the oil in the crankcase in engines equipped with oil dilution systems. However, fuel can also be too volatile, causing detonation and vapor lock. AVGAS is a blend of numerous hydrocarbon compounds, each with different boiling points and volatility. A straight chain of volatile compounds creates a fuel that vaporizes easily for starting, but also delivers power through the acceleration and power ranges of the engine.Vapor LockVapor lock is a condition in which AVGAS vaporizes in the fuel line or other components between the fuel tank and the carburetor. This typically occurs on warm days on aircraft with engine-driven fuel pumps that suck fuel from the tank(s). Vapor lock can be caused by excessively hot fuel, low pressure, or excessive turbulence of the fuel traveling through the fuel system. In each case, liquid fuel vaporizes prematurely and blocks the flow of liquid fuel to the carburetor.Aircraft gasoline is refined to have a vapor pressure be between 5.5 pounds per square inch (psi) and 7.0 psi at 100 °F. At this pressure, an aircraft fuel system is designed to deliver liquid fuel to the carburetor when drawn out of the tank by an engine-driven fuel pump. But temperatures in the fuel system can exceed 100 °F under the engine cowl on a hot day. Fuel may vaporize before it reaches the carburetor, especially if it is drawn up a line under a low pressure, or if it swirls while navigating a sharp bend in the tubing. To make matters worse, when an aircraft climbs rapidly, the pressure on the fuel in the tank decreases while the fuel is still warm. This causes an increase in fuel vaporization that can also lead to vapor lock.Various steps can be taken to prevent vapor lock. The use of boost pumps located in the fuel tank that force pressurized liquid fuel to the engine is most common. Carburetor IcingAs fuel vaporizes, it draws energy from its surroundings to change state from a liquid to a vapor. This can be a problem if water is present. When fuel vaporizes in the carburetor, water in the fuel-air mixture can freeze and deposit inside the carburetor and fuel induction system. The fuel discharge14-7。
中英文文献翻译—燃油喷射系统及点火系统
英文文献与中文参考译文A1Fuel injection systemsA1.1 General informationFuel injection systems have been used on vehicles for many years. The earliest ones were purely mechanical. As technology advanced, electronic fuel injection systems became more popular. Early mechanical and electronic fuel injection systems did not use feedback controls. As emissions became more of a concern, feedback controls were adapted to both types of fuel injection systems. Both mechanical and electronic fuel injection systems can be found on gasoline engines.A1.2 Multi-port fuel injectionsThis is the most common type of fuel injection system found today. Regardless of the manufacturer, they all function in the same basic way. On these systems an equal amount of fuel is delivered to each cylinder.These systems all use sensors which transmit operating conditions to the computer. Information from these sensors is processed by the computer which then determines the proper air/fuel mixture. This signal is sent to the fuel injectors which open and inject fuel into their ports. The longer the injector is held open, the richer the fuel mixture will be. Most fuel injection systems need the following information to operate properly.Temperature sensors-this includes both air and coolant temperature. The computer determine how rich or lean the mixture should be. The colder the temperature, the richer the mixture.Throttle position sensors or switches-the computer uses this information to determine the position of the throttle valve(s). Some vehicles use sensors which relay the exact position of the throttle valve(s) at all times. Others use switches which only relay closed and wide-open throttle positions (some may also use a mid-throttle switch). These switches and sensors help determine engine load.Airflow sensors-these sensors also help the computer determine engine load by indicating the amount of air entering the engine. There are several different types of airflow sensors, but in the end, they all do the same job.Manifold pressure sensors-if a vehicle is not equipped with an airflow sensor, ituses a manifold pressure sensor to determine engine load (Note that some vehicles with an airflow sensor may also have a manifold pressure sensor. This is used as a fail-safe if the airflow sensor fails). As engine load increases, so does intake manifold air pressure.Engine speed and position sensors-engine speed/position sensors can be referenced form the crankshaft, camshaft or both. In addition to helping determine engine load, these sensors also tell the computer when the injectors should be fired.These systems operate at a relatively high pressure(usually at least 30 psi). To control the fuel pressure, a fuel pressure regulator is used. As engine load increases, more fuel pressure is needed. This is due to the richer mixture (more fuel needed) and to overcome the increased air pressure in the ports. Any unused fuel is diverted back to the fuel tank using a return line.A2. Ignition systemThere are many different types of ignition systems. Most of these systems can be placed into one of three distinct groups: the conventional breaker point type ignition systems (in use since the early 1900s); the electronic ignition systems (popular since the mid 70s); and the distributorless ignition system (introduced in the mid 80s).The automotive ignition system has two basic functions: it must control the spark and timing of the spark plug firing to match varying engine requirements, and it must increase battery voltage to a point where it will overcome the resistance offered by the spark plug gap and fire the plug.A2.1How does the ignition system workAn automotive ignition system is divided into two electrical circuits—the primary and secondary circuits. The primary circuit carries low voltage. This circuit operates only on battery current and is controlled by the breaker points and the ignition switch. The secondary circuit consists of the secondary windings in the coil, the high tension lead between the distributor and the coil (commonly called the coil wire) on external coil distributors, the distributor cap, the distributor rotor ,the spark plug leads and the spark plugs.The distributor is the controlling element of the system. It switches the primary current on and off and distributes the current to the proper spark plug each time a spark is needed. The distributor is a stationary housing surrounding a rotating shaft.The shaft is driven at one-half engine speed by the engine’s camshaft through the distributor drive gears. A cam near the top of the distributor shaft has one lobe for each cylinder of the engine. The cam operates the contact points, which are mounted on a plate within the distributor housing.A rotor is attached to the top of the distributor shaft. When the distributor cap is in place, a spring-loaded piece of metal in the center of the cap makes contact with a metal strip on top of the rotor. The outer end of the rotor passes very close to the contacts connected to the spark plug leads around the outside of the distributor cap.The coil is the heart of the ignition system. Essentially, it is nothing more than a transformer which takes the relatively low voltage (12 volts) available from the battery and increases it to a point where it will fire the spark plug as much as 40000 volts. The term “coil” is perhaps a misnomer since there are actually two coils of wire wound about an iron core. These coils are insulated from each other and the whole assembly is enclosed in an oil-filled case. The primary coil, which consists of relatively few turns of heavy wire, is connected to the two primary terminals located on top of the coil. The secondary coil consists of many turns of fine wire. It is connected to the high-tension connection on top of the coil (the tower into which the coil wire from the distributor is plugged).Under normal operating conditions, power from the battery is fed through a resistor or resistance wire to the primary circuit of the coil and is then grounded through the ignition points in the distributor (the points are closed). Energizing the coil primary circuit with battery voltage produces produces current flow through the primary windings, which induces a very large, intense magnetic field. This magnetic field remains as long as current flows and the points remain closed.As the distributor cam rotates, the points are pushed apart, breaking the primary circuit and stopping the flow of current. Interrupting the flow of primary current causes the magnetic field to collapse. Just as current flowing through a wire produces a magnetic field, moving a magnetic field across a wire will produce a current. As the magnetic field collapses its lines of force cross the secondary windings, inducing a current in them. Since there are many more turns of wire in the secondary windings, the voltage from the primary windings is magnified considerably up to 40000 volts[18,19].参考译文：A1.燃油喷射系统A1.1 燃油喷射系统概述燃料喷射系统已经在汽上车使用了许多年。
飞机状态显示面板翻译
BIP飞机状态显示面板eng fire：引擎失火eng 2 fire: 2 号引擎失火eng 3 fire：2 号引擎失火eng 4 fire:4号引擎失火oil pressure: 引擎油压力eng 1 oil pressure：1号引擎油压力eng 2 oil pressure：2号引擎油压力eng 3 oil pressure：3号引擎油压力eng 4 oil pressure：4号引擎油压力eng oil temp：引擎油温度eng 1 oil temp：1号引擎油温度eng 2 oil temp：2号引擎油温度eng 3 oil temp：3号引擎油温度eng 4 oil temp：4号引擎油温度fuel low：燃油低down：下降UP: 上升left eng fire ：左引擎失火right eng fire：右引擎失火low pressure：低压力oil pressure：油压力eng 1 oil pressure：1号引擎滑油压力beacon light：信标灯com 1：com 2：dme：mkr：both：ap master：adf：自动方位搜寻器centre fuel low: 中心燃油低fuel cross feed:gear up: 放起落架gear down:收起落架auto pilot: 自动驾驶仪gear unsafe: 闸不安全master caution: 主警告master warning:主警报strobe light: 频闪灯landing lights: 落地灯parking brakes: 停车制动器pitot heat: 皮托管加热rotor low rpm:转子低转速stall warning: 失速警告door warning: 门警告vac low: 低空nav: 导航模式gps:gps定位nav 1:导航台1 nav 2：导航台2 com 1:通讯电台1 com 2: 通讯电台2 NAV 1:导航台1NAV 2:导航台2 ADF:ADF导航台 DME是测距仪Alt:高度,海拔vs:失速速度ias:指示空速hdg:航向crs:航道Ap:自动驾驶hdg: 航向nav:导航apr rev:修改,修正Alt:高度,海拔crs :航道ias:指示空速auto throttle:自动油门flapsthrottle:节流阀prop:螺旋桨飞机mixture:混合物。
飞机燃油系统
飞机燃油系统【摘要】飞机燃油系统是飞机上众多系统中的一个子系统，它的功用是储存燃油，并保证在规定的任何状态（如各种飞行高度、飞行姿态）下，均能按发动机所要求的压力和流量向发动机持续不间断地供油。
此外，燃油系统还可以完成冷却飞机上其他系统、平衡飞机、保持飞机重心于规定的范围内等附加功能。
民用飞机燃油系统一般包括燃油箱系统、加放油系统、供输油系统、油箱通气增压系统、燃油测量系统、信号指示系统和热负载系统。
关键词：飞行高度、燃油系统、加放油系统、供输油系统、信号指示系统、热负载Abstract : Aircraft aircraft fuel system is a subsystem of many systems, its function is to store fuel, and ensure that the provisions of any state (such as various flight altitude, flight attitude), the engine can pressthe required pressure and flow continued uninterrupted fuel supply to the engine. In addition, the fuel system can also complete the rest of the aircraft cooli ng system, the bala nee of the aircraft, main tai n aircraft cen ter of gravity in the con text of the provisi ons of other additi onal features. General civil aircraft fuel system including fuel tank system, add the oil drain system for the oil system, fuel tank ventilation pressurization system, fuel measurementsystems, signal indicator system and the heat load system.Keywords: aircraft fuel system; Development目录1飞机燃油系统的概述 (2)1.1燃油系统的功用 (2)1.2燃油系统的特点 (2)2飞机燃油系统的组成 (3)2.1燃油通气系统 (4)2.1.1燃油箱通气系统的作用 (4)2.1.2通气系统的组成和工作原理 (4)2.2加油系统 (5)2.3应急放油系统 (6)2.4供油系统 (7)2.4.1飞机的供油方式 (7)2.4.2燃油测量系统 (8)2.5燃油箱油量指示系统 (9)3航空燃油 (11)3.1 航空汽油 (11)3.2航空煤油 (11)4燃油系统附件 (12)4.1燃油箱 (12)4.2增压泵 (12)4.3引射泵 (12)5燃油测量系统的发展趋势 (13)结束语 (14)谢辞 (14)文献 (16)1飞机燃油系统的概述飞机燃油系统是飞机上众多系统中的一个子系统，它的功用是储存燃油，并保证在规定的任何状态（如各种飞行高度、飞行姿态）下，均能按发动机所要求的压力和流量向发动机持续不间断地供油。
民航专业文献客机燃油系统
一客机燃油系统1.功用飞机燃油系统储存一定量地燃油,并根据需要可靠地将燃油供应到发动机和辅助动力装置（APU）.2.组成飞机地燃油系统包括燃油箱.通气系统.加油系统.供油系统.抽油系统.燃油交输系统和燃油指示系统.2.1燃油箱：B737-300飞机有3个燃油箱（中央油箱和1号.2号主油箱）和2个通气油箱2.2容量:1号和2号主油箱地储油量为5674L,中央油箱地储油量为8755L.每个油箱地容积都大于储油量,以保证燃油膨胀和油箱通气.通气油箱在正常情况下是空地,加油过量时能容纳113.56L燃油.2.3结构:B737-300飞机地油箱是结构油箱,充分利用机翼内地空间.1号.2号主油箱内地翼肋和中央油箱内地展向梁腹板可减少燃油晃动.一些翼肋上地挡板单向活门保证靠翼根地增压泵入口始终有油.2.4接近盖板:在机翼下表面有一系列接近盖板,1号.2号主油箱各有12个,中央油箱有1个,通气油箱各有2个.接近盖板为每个油箱提供检查通道,翼肋和展向梁上地较大开口使得维修时可接近油箱地各个角落.另外,每个机翼上有2个小一些地盖板用来接近燃油增压泵.3.油箱排放活门3.1位置：主油箱.中央油箱.通气油箱各有一个排放活门,装在每个油箱地最低点.3.2功用：用来排出油箱沉淀槽内地积累杂质或排空油箱.3.3操作：主油箱和通气油箱排放沉淀时,使用专用工具.当用工具往上顶活门时,可打开活门,放出沉淀.中央油箱放油时,先通过两个空调舱之间地一块盖板接近排放活门,然后拉动钩子打开活门放油.松开钩子,活门就关闭.3.4注意：拆下中央油箱和通气油箱地排放活门时,不用放油.拆下主油箱排放活门时,需要放油.4.油箱通气4.1功用：油箱通气系统使得飞机在任何姿态时,油箱都能和大气相通,保证油箱里面有高地空气压力,确保向发动机顺利供油.4.2组成：通气系统包括通气油箱.通气斗.通气管道.单向活门和浮子活门等.4.3通气：通气管道是机翼上壁板地长桁.飞机平飞和下降时,油箱通过正常通气口通气.通气口带有浮子活门,油面上升时关闭,防止燃油进入通气管道,油面下降时通气.飞机爬升时,油箱通过靠前部地爬升通气口通气,通气口带有单向活门.4.4储油：如果加油时出现溢流,通气油箱能储存30美加仑地燃油.中央油箱油面下降后,这部分燃油可通过中央油箱通气管道流入中央油箱.4.5通气斗：在两个外通气油箱下翼面上,各用螺钉安装了1个通气斗.通气斗在飞行中可利用冲压效应为油箱增压.5.APU套管排放5.1功用：APU供油管地外面有一个套管,套管防止APU供油管路破裂时燃油泄漏到飞机内部.在靠近轮舱.套管最低处,通过一条排放管连接到左翼身整流罩地排放口.正常情况下,排放积水,如果套管里有燃油,可通过排放管排出机外.5.2火焰抑制器：安装在排放总管上,防止外来火焰进入排放管道. 5.3排放龙头：是一个开关,在地面时,可打开龙头,以检查和排放泄漏地燃油.在飞行中,排放龙头必须关闭.6.加油6.1重力加油重力加油口：在两机翼上表面各有一个重力加油口,加油口附近有接地插孔.操作：打开重力加油口盖子,插好接地线后,可以通过重力直接往主油箱加油,但加不满.中央油箱可通过燃油转换得到燃油.注意：飞机进行压力加油时,不要打开重力加油口盖子,以免燃油从机翼上面重力加油口流出.6.2压力加油：压力加油通过右机翼前缘下部地加油站进行,可对三个油箱进行满油量加油.每个油箱有一个浮子电门来感受各油箱地满油状态.6.3加油站：位于右机翼下翼面靠前缘处.加油站部件有加油站盖板.加油控制面板（P15）.照明灯.加油接头.加油站电源开关.内话插孔.接地插孔等.6.4电源控制：加油站盖板作动加油站电源开关.当加油站盖板打开时,电源接通,3个白色照明灯点亮.如果打开盖板时,照明灯不亮,可以通过加油控制面板上地辅助加油电源控制电门接通电源.6.5加油控制面板：加油控制面板包括3个油量指示表.3个加油控制电门.3个活门位置指示灯和1个油量表测试电门（或辅助加油电源控制电门）.位置指示灯指示活门在打开位.加油控制电门用于打开和关闭加油活门.电门放“OPEN”位时,位置灯亮,活门地打开需要燃油压力作动.当加油活门上地电磁阀失效时,可用人工超控柱塞打开.油量表指示对应油箱地燃油重量.油量表测试电门用于在加油之前,测试油量表,还用于当加油站电源开关失效时,进行辅助电源控制.6.6加油接头：加油接头内有一弹簧加载关闭地活门,加油软管接上时即被顶开,当加油管道断开时关闭,防止燃油倒流.6.7加油注意事项：加油压力不能超过55 PSI .要使用规定牌号地燃油.燃油箱地满油量是：主油箱1499 US.GAL,中央油箱2313 US.GAL .6.8加油操作说明：插入接地线,取下接头盖子并连接加油软管.测试油量表和活门位置灯.把控制电门放“OPEN”位,燃油压力打开活门,燃油开始流动.当达到所需油量时,把控制电门板到“CLOSED”位置,关闭活门.或者当油箱加满时,自动关断活门.飞行前,必须把控制电门放“CLOSED”位,活门关闭,位置灯灭.6.8.1加油总管：功用：加油总管是压力加油.抽油和燃油转换地分配中心.组成：包括3个加油活门和3个单向活门.6.8.2加油活门工作：加油活门控制加油时地燃油流动.当连接加油软管时,管接头里地柱塞顶开加油接头里地提升阀.燃油进入加油总管,同时燃油通过小孔还进入膜盒内腔,使得加在膜盒上地压力相同,活门在弹簧力作用下关闭.当电磁阀通电工作（或按压人工超控活塞并锁住）时,膜盒内腔地燃油流入加油管道,膜盒内腔地压力下降,燃油压差作用力克服弹簧力,使活门打开,燃油从总管通过单向活门流入相应地油箱.当电磁阀断电（或松开人工超控柱塞）时,膜盒内腔地压力又上升,膜盒上地压力趋于相等,活门在弹簧力作用下关闭.6.8.3单向活门：单向活门防止燃油倒流.6.8.4加油管道：2号油箱加油管道上有一个限流器,保证和1号油箱加油同步.中央油箱加油管道上有两个支路到两个中央油箱增压泵,向增压泵注油.6.8.5浮子电门：功用：每个油箱有1个浮子电门,防止油箱加油时向外溢油.安装：浮子电门安装在靠近每个油箱顶部,以感应满油量.通过油箱检查盖板,可接近浮子电门.工作：在压力加油过程中,当油箱未加满时,浮子电门闭合,加油活门地电路接通,加油活门保持打开.当油箱加满时,浮子电门断开加油活门地电路,加油活门关闭,加油停止.7.供油7.1功用：供油系统把油箱地燃油供到发动机和APU.7.2组成：供油系统包括增压泵.引射泵.供油总管.旁通活门.交输活门.燃油关断活门等.7.3燃油控制面板组成：燃油控制面板上有6个增压泵控制电门.6个低压警告灯.2个燃油滤旁通警告灯.1个交输活门控制电门.1个交输活门打开位置指示灯.1个燃油温度表和2个燃油活门关闭位置指示灯.功用：增压泵控制电门操作对应地燃油泵,当控制电门扳到“ON”位时,燃油泵工作,当控制电门扳到“OFF”位时,燃油泵关断.琥珀色低压警告灯为对应燃油泵地低压力提出警告.交输活门控制电门控制交输活门位置,蓝色位置指示灯指示活门在未关状态.燃油温度表指示1号主油箱地燃油温度.燃油关断活门位置指示灯（蓝色）指示对应发动机燃油关断活门不在打开状态.7.4其它指示和控制：P7板上琥珀色地主警告灯和信号牌上地“FUEL”警告灯在某个油箱地两个增压泵出口都处于低压状态时点亮.中央操纵台上地起动手柄控制燃油关断活门位置.起动手柄提起时,燃油关断活门打开.当P8-1板上地灭火手柄提起时,可关断对应发动机地燃油关断活门.7.5增压泵位置：每个油箱有两个燃油增压泵,主油箱地前增压泵装在机翼前梁上,主油箱后增压泵和中央油箱增压泵装在干燥舱里.结构.工作：增压泵是由三相交流马达驱动地离心式叶轮泵,泵出口有单向活门,防止燃油倒流,并保证正确地供油顺序：先中央,后两边（因为中央油箱单向活门地打开压力差比主油箱单向活门地要低一些）.单向活门结构不同,防止错装.单向活门上游有低压警告电门地传感油路.主油箱前增压泵还有往引射泵地供压管道.为提高供油系统地工作可靠性,6个增加泵地工作电流和控制电流都来自不同地汇流条.维护：增压泵进口有一拆卸活门,可通过外部地操纵手柄来控制,拆卸油泵时,先把拆卸活门关闭,然后通过泵下部地放油口放出泵内地燃油,即可拆下油泵,不用对油箱放油.安装油泵前,要往泵内注油,装好后必须把拆卸活门打开,否则,接近盖板装不上.7.6燃油关断活门位置：装在机翼前梁上,打开时向发动机供油.控制：由起动手柄控制其打开.关闭.灭火手柄提起时能关闭活门.指示：燃油控制面板（位于P5板）上地位置灯指示其状态.活门关闭状态时暗亮,活门转换过程中明亮,活门打开状态时灯灭.维护：人工超控手柄提供人工操纵,并指示活门位置.拆卸活门时,要把油箱内燃油放至800 US.GAL.7.7燃油交输活门位置：装在右机翼地后梁上,可从右主轮舱接近,打开时,左右供油总管连通,实现交输供油.控制：由燃油控制面板（P5-2）上地控制旋钮控制.指示：活门打开指示灯指示活门状态.当活门关闭状态时灯灭,当活门转换过程中灯明亮,当活门打开状态时灯暗亮.维护：人工超控手柄提供人工操纵,并指示活门位置.拆卸活门时,要把2号主油箱放油到250 US.GAL.7.8引射泵7.9旁通活门位置：每个主油箱有一个旁通活门把主油箱和供油总管直接连通.功用：当油箱里压力高于供油总管压力时,燃油经旁通活门供往发动机,即重力供油.8.抽油8.1抽油活门：抽油活门位于右机翼前梁,靠近加油站.只能人工打开,所以只能地面抽油.拆卸活门时,要把2号主油箱放油到800 US.GAL.8.2抽油操作：抽油时,在加油接头上连接一根油管,打开抽油活门,打开对应油箱地增压泵,则此油箱地燃油就被抽到机外.对1号主油箱和中央油箱抽油时,需打开交输活门.也能用外部吸力在增压泵不工作时抽油,但不可取,一般不用.9.燃油交输功用：当某个主油箱地2个增压泵都失效时,通过交输活门可以实现一个油箱向两个发动机供油.当1号主油箱地增压泵都失效时,打开交输活门,2号主油箱可以向两个发动机供油.10.燃油转换功用：飞机在地面,如果需要平衡油箱地油量（或需要对某个油箱放油,但没有抽油设备）时,可通过增压泵.抽油活门和加油活门（有时也用交输活门）在油箱间实现燃油转换.例：当从1号主油箱向中央油箱转换燃油时,需：（1）打开1号油箱增压泵；（2）打开交输活门；（3）打开抽油活门；（4）打开中央油箱加油活门.11.燃油指示11.1功用：燃油指示系统用于测量和指示燃油温度及各油箱油量.11.2燃油量指示指示器位置：燃油量指示表在P15板和P2板,CDU上有总油量显示.附件位置：每个主油箱有12个油箱测量元件和1个补偿元件,中央油箱有2个油箱测量元件和1个补偿元件,油箱内电缆把它们全部连接在一起,并由机翼前梁（主油箱）和左轮舱前壁板（中央油箱）上地插头,把信号传递到油量处理器和加法器,油量在指示表和CDU上显示.工作原理：测量元件是圆柱形电容器,同轴地圆柱电极之间是空地,用燃油和油气混合气作为电介质.油面高度不同,液体和气体地比例不同,电介常数变化,电容也变化.所以,测量了电容大小,就知道了燃油地容积.由于许多测量元件,分布在油箱各个位置,因此,保证飞机在各种姿态时,都能测量到准确地燃油容积.补偿元件是始终浸没在燃油里地电容器,它地电容大小完全由燃油密度决定.因此由补偿元件地电容,可以确定燃油地密度.燃油量处理器把测量元件地信号和补偿元件地信号综合计算后,得到油箱地重量数据,并在指示器上显示.电容调节器能调整油箱总电容,使可以更换不同地油量表.加法器把3个油箱地油量加起来,得到飞机地总油量,并把数据提供给飞行管理计算机（FMC）和在控制/显示组件（CDU）上显示.油量处理器内地微处理机还监控系统工作,当部件有故障时,提供对应地故障代码,在指示器上显示,帮助查找故障.机械式测量油尺：主油箱内各有5个油尺,可在没有电源地情况下,检查主油箱油量,分别位于机翼下表面地1.4.6.8和10号油箱个人收集整理资料，仅供交流学习，勿作商业用途盖板内.油尺属于下拉式磁性浮子油尺.使用时,松开油尺地锁机构,油尺在重力作用下下坠,当磁性力平衡重力时,油尺保持一固定伸出量.此时,油尺上地刻度表示油量.测量油尺资料中地容量表格作为飞机姿态修正.11.3燃油温度指示温度探头：燃油温度探头通过左机翼后梁伸入1号油箱,感受燃油温度.其电阻随温度不同而变化,作为电桥电路地一部分.拆卸探头时无需放油.温度指示器：燃油温度指示器是一个电桥电路,由无电清除线圈.偏转线圈.座舱温度补偿器.刻度盘等组成.电源为28V AC,由28V AC BUS 2提供.整流后,经无电清除线圈提供给电桥.在没有电源时,无电清除线圈失去电磁力,永磁铁地磁性力就把指示表地指针驱动到最左端（-56℃）位置,指示表地刻度范围-56℃—56℃,位于P5-2面板.维护：维护检查时,可在温度传感器上施加一定温度,用一个标准温度计来测量此温度,并和指示器温度相比较,来确定温度指示系统是否正常工作.。
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飞机燃油系统姓名：温可明学号：10063121南昌航空大学飞行器工程学院【摘要】飞机燃油系统是飞机上众多系统中的一个子系统，它的功用是储存燃油，并保证在规定的任何状态（如各种飞行高度、飞行姿态）下，均能按发动机所要求的压力和流量向发动机持续不间断地供油。
此外，燃油系统还可以完成冷却飞机上其他系统、平衡飞机、保持飞机重心于规定的范围内等附加功能。
民用飞机燃油系统一般包括燃油箱系统、加放油系统、供输油系统、油箱通气增压系统、燃油测量系统、信号指示系统和热负载系统。
关键字：燃油系统供输油系统油箱燃油特性腐蚀安全与排故正文一：燃油系统的组成作为一个燃油系统,必须有至少油箱、管道、油过滤器、截止阀和油、规模等,简单的燃油供给系统是依靠重力活塞引擎油系统。
油箱高度相对于化油器,印版压力,使汽油可以达到化油器。
有一个加油在背心,也是油箱通气。
下水道在内胆底部的,它也是一个排污口。
有一个关闭阀、防火阀在油滤器过滤后。
另一个开始泵用于石油在启动。
燃油系统由油箱,油箱通风系统、气/油应急放油系统、燃料供给系统、压缩空气系统和指令/预警系统等。
二：燃油系统的功能（1）：储存燃油（2）：在规定的飞行条件下的安全可靠传输燃料发动机和生产现场的安全、可靠（3）：调整重心位置,保持平衡和压力的机翼结构（4）：制冷配件,如冷却源三：燃油系统的特点（1）：大燃料载荷（2）：供油安全（3）：可以删除油泵不放油泵快速放电,提高维护性能（4）：可视化的燃料控制面板（5）：避免死油（6）：使用压力加油（7）：通风油箱（8）；紧急卸油系统四：燃油系统的要求（1）燃油增压泵一般安装在油箱的最低点，保证起飞、着陆、启动和高空都能有效工作，还要有足够的能力当发动机驱动的油泵失效时以替代之。
（2）当增压泵全部失效时，依靠重力供油，靠发动机驱动的油泵的抽吸作用，仍能向发动机供油。
（3）每个油箱至少有两台增压泵。
对于任何正常飞行姿态下的燃油载荷，每个油箱至少有一个油泵能泵出燃油。
（4）多发动机的燃油系统，应是从各自相应的油箱供油。
应急时，可以从一个油箱向所有发动机供油。
（5）：燃油系统应是可交叉供油的，但不能在油箱间有溢流。
（6):油箱应通气。
通气系统应在任何飞行状态下都能提供足够的通气流量，且能防止燃油从通气管道溢出。
通气系统应使油箱内有正压，不出现负压，以保证增压泵运转正常。
(7):应有水分收集和排水设施，以排除积水和受污染的脏油。
(8):应设通气集油箱，阻止燃油向机外溢出，收集到的燃油在主油箱耗去大部分燃油后，靠重力流入主油箱。
(9):燃油管道的尺寸应保证通过最大流量，且没有小半径的弯折和急剧的弯曲上升或下降，因为这些地方会引起蒸气的集聚而导致气塞。
(10):所有油箱的内部、外部和附件都是可以接近的，以便维修。
五：油箱的类型飞机油箱的作用是存储飞机所需的燃油。
飞机油箱有三种类型，即软油箱、硬油箱和结构油箱。
（1）软油箱软油箱是用耐油橡皮、胶层和专用布等胶合而成，一般应用在老式飞机和某些单翼飞机的中央油箱上。
目前，软油箱在大型民航运输机上已很少采用。
（2）硬油箱由防腐能力较强的铝锰合金制成箱体，箱内有防止油液晃动的带孔隔板，隔板可以提高油箱强度和刚度。
目前，硬油箱通常作为大型飞机的中央辅助油箱。
（3）结构油箱飞机的油箱大多采用结构油箱，即利用飞机机身、机翼或尾翼的结构元件直接构成的油箱，如图2所示。
结构油箱又被称为整体型油箱。
整体型油箱是飞机结构的一部分，因此在接缝、结构紧固件和接近口盖等处应妥善密封。
结构油箱的优点结构油箱内的翼肋可防止油液发生晃动，翼肋底部有单向活门，使油液由翼尖流向翼根。
结构油箱的特点是可充分利用机体内的容积，增大储油量，并减小飞机的重量。
六：油箱的布置一架飞机上会布置多个油箱，即中央油箱和机翼主油箱，在主油箱外侧还设有通气油箱。
有些飞机还配有机尾配平油箱和中央辅助油箱。
（1）中央油箱中央邮箱位于中央翼盒内，油箱内的隔板可防止飞机在机动飞行时燃油发生晃动。
飞行中，为减小机翼根部所受的弯矩，中央油箱的油液应首先使用。
当油箱中油液耗空时，油箱内充满燃油蒸汽。
当燃油蒸汽浓度在着火（爆炸）浓度范围内时，遇到高温或火花（静电或通过油箱的电缆故障）会导致油箱起火爆炸。
为消除油箱起火爆炸的危险，设计中央油箱时必须考虑加装惰性气体抑爆系统或设置无油干舱。
某些飞机采用了其他解决办法，即取消独立的中央油箱，沿飞机纵剖线将中央油箱分开，分别与左右主油箱相通，构成双油箱布局。
此种设计虽然省略了中央油箱惰性气体抑爆系统，但飞行中机翼受力情况不如三油箱布局。
（2）主油箱机翼上的结构油箱称为主油箱，一般将左侧主油箱称为1号主油箱，右侧主油箱称为2号主油箱。
主油箱上表面一般都有重力加油口，下表面装有数个油尺。
主油箱内的翼肋可防止油液发生晃动，翼肋底部有单向活门，使油液由翼尖流向翼根。
为了减小翼吊发动机对主油箱的影响，某些飞机在其主油箱的发动机上方的高温区域设置了干舱。
干舱内不存储燃油，因此干舱内不会存在燃油蒸汽，从而达到了防火的目的。
图3所示为波音777飞机的油箱干舱系统。
为了防火，波音777设置了三个干舱，即中央油箱干舱和左右大翼干舱。
（3）通气油箱通气油箱位于主油箱外侧、靠近翼尖的区域内。
通气油箱内不装燃油，仅用于油箱的通气。
（4）配平油箱某些大型飞机有配平油箱。
配平油箱装在飞机尾部，一般安装在水平安定面内。
在飞行中，燃油管理系统可根据需要将燃油送入（或排出）配平油箱，调整飞机重心的位置，减小飞机平尾配平角度，降低配平助力，达到提高飞机燃油经济性的目的。
（5）中央辅助油箱中央辅助油箱作为飞机正常油箱系统的补充，用于提高飞机的航程。
中央辅助油箱外形和标准货运集装箱类似，安装在飞机的前后货舱内，通过专用的供油管路和通气管路与飞机燃油系统相连。
在飞机内配置辅助中央油箱时，应注意对飞机重心的影响。
七：渗漏的原因和检查1). 渗漏产生的原因（1）不正确的接头连接、安装；（2）紧固件松动；（3）密封圈损坏；（4）密封剂问题；（5）密封剂损坏；（6）表面处理不当，即表面有油脂、金属屑、刷毛等。
这些外来物导致密剂不能紧密结合。
（7）密封剂混合和保存不正确。
密封剂一般包括两个部分，即基体材料和加速剂，如果其混合比例不正确，则会影响密封效果，而且密封剂都有一定的寿命，在一定时间后，应测试密封剂是否能够继续使用。
（8）密封剂使用不当。
没有严格按密封剂使用操作规程操作有可能导致密封效果变差，导致燃油泄露。
2).渗漏的检查（1）气压发泡剂检查法（2）空心螺栓气泡检查法（3）空心螺栓染色剂喷射法（4）气压检查法八：油箱腐蚀问题当槽相配,细菌会出没在石油。
碳氢化合物在燃油和溶解在油物质如氮、氧、硫、磷、和提供各种各样的细菌生活在物质基础;水在燃料来提供合适的环境,细菌的生长,细菌通常生活在燃油和水界面;适当速度的温度将加速繁殖的细菌,细菌的最适生长温度为25℃~ 30℃。
微生物育种在燃油将导致损失的燃料质量,形成黑泥沉积在燃料。
沉积物会引起很大的影响燃油系统:塞油泵和油过滤器、吸油口导致石油供应系统故障;堵塞燃油传感器,油量指示系统故障;污染物不能及时清理,导致腐蚀的坦克。
研究表明,微生物腐蚀是主要形式的腐蚀槽结构。
为了消除微生物污染的影响在燃料系统和腐蚀的坦克,必须破坏细菌繁殖环境,控制增长速度。
现在唯一要做的就是控制燃料中的水分。
水分在燃油不仅会创造一个舒适的环境为微生物的生长,也会直接的负面影响飞机燃油系统。
因此在水系统和燃油系统是安装在水箱水定期。
九：检查飞机燃油系统密封这项检查是在飞机各油箱加满油，利用地面冷气瓶的冷气，使油箱增压到24.5kPa（0.25kgf/com）的条件下进行的。
检查的目的是判明飞机油箱增压管路是否漏气和输油部分是否漏油。
打开地面冷气瓶的开关，然后缓慢地打开地面增压箱的供气开关，向飞机各油箱充气增压，当油箱内的气压上升到24.5kPa（0.25kgf/cm2）时，先关闭地面增压箱供气开关，再关闭冷气瓶的开关，然后保持10分钟，要求油箱内气压下降不得超过1.9kPa（0.02kgf/cm2），各油箱和接头处不应有漏油现象。
检查时，要特别注意查看5、6油箱底部，以及连通管结合处有无裂纹和漏油。
因为它们处于发动机舱高温区，易于损坏。
检查完毕，拆下地面增压箱，取下所有的堵盖、堵塞，安装好机身油箱增压安全活门和各导管接头，然后查看油门手柄确实在停车位置后，打开防火开关，并接通1、2、3油泵工作2～3分钟，要求油箱和各导管接头不应当漏油，各信号装置指示正常。
十：结束语写论文是一个不断学习的过程，从最初刚写论文时对飞机燃油系统系统的模糊认识到最后能够对该问题有深刻的认识，我体会到实践对于学习的重要性，以前只是明白理论，没有经过实践考察，对知识的理解不够明确，通过这次的做，我真正体会到飞机燃油系统系统的意思，使我对飞机燃油系统系统有了一个比较深刻的认识。
总之，通过这次论文,我深刻体会到要做好一件事并不是那么容易，不仅需要有坚持不懈和不厌其烦的精神，而且还需要有解决问题的能力。
对待要解决的问题，要有耐心、有毅力，要善于运用已有知识和资料来充实自己，使自己获得更多的进步，同时我也深刻的认识到，在对待一个新的问题时，一定要从整体考虑，完成一步之后再作下一步，这样才能更加有效。
路漫漫其修远兮，吾将上下而求索，为了更好的生活，我将不断的学习，向着更高的目标前进。