航空工程英语基础_机务人的宝典

1、ESSENTIAL（基础） ENGLISH OF AERONAUTICAL ENGINEERING航 空 工 程 英 语 基 础LESSON 1 THE B737 FUSELAGE机体 一、生词飞机 起落架 分为 玻璃纤维 铰链 进口电子设备舱 货舱 空间Airplane Landing gear Divide into Fiberglass Hinge Entry Electronic equipment bay Cargo Space unit排出 伸长 增强 结构Exhaust stretch Strengthen structure设计 延伸 相对于 修改 逃逸 燃油箱power 水平

2、安定面Escape Fule bank Horizontal stabilizer Design Extension Relaviate to revise和一样 脊鳍 滑轨The same as Dorsal fin Skid舱口 终止 桁架半硬壳式 动力装置 包括 蜂窝状物 压力密封隔板 机上厨房 检修口Galley Access door登机梯 旅客舱Semi-monocoque 机身 Power plant Contain Honeycomb Bulkhead支柱 天线 整流罩 驾驶舱Fuselage Strut Antenna Fairing flight compartment A

3、irstair Passenger cabin Hatch Terminate Truss辅助动力装置 Auxiliary二、TEXT(1) the B737 is a low wing airplane. B737 has semi-monocoque fuselage and fully retractable landing gear. Two power plants are located under the wings on short struts.波音737是一种下单翼飞机。它拥有半硬壳式机身和全收式起落架。两台发动机位于机翼下方短支架上。(2) The 737-300 fus

4、elage is divided into four sections: section 41 , section 43 , section 46 and section 48 .波音737机体为为四部分：41、43、46和48.(3) Section 41 contains the radar antenna behind a fiberglass honeycomb fairing, hinged at the top. aft of the pressure bulkhead, above the floor, are the flight compartment and forward

5、 airstair and its door, and the electronic equipment bay .this section has two lower access doors.41部分包括铰接在蜂窝状玻璃纤维雷达罩后面顶部的雷达天线、压力隔板后方及地板上方区域是驾驶舱和前登机梯及其门，还有电子设备舱。这部分有两个下检修口。(4) Section 43 contains the passenger cabin and the forward cargo compartment.43部分包括客舱和前货舱。(5) Section 46 contain the center and

6、 aft portion of the passenger cabin ,two overwing escape hatches and aft entry and service doors. The space below the floor includes the wing center section (fule tank), air-conditioning bays, wheel well, hydraulic bay and aft cargo compartment. this section terminates at the aft pressure bulkhead.4

7、6部分包括客舱中后部，两个逃生舱及入口和服务门。地板下的空间包括中央油箱、空调舱、轮舱、液压舱和后货舱。这部分终止于后压力隔板。(6) Section 48 contains the auxiliary power unit(APU) and horizontal stabilizer truss. Access to this section is through a door on the left side. Aft of which is the APU access door and APU exhaust.48部分包括辅助动力装置和水平安定面桁架。可以通过左侧口盖接近。在它们的后面

8、是APU检修口和APU排气口。(7) The 737-300 is the same basic design as the 737-200, with a body stretch of 104 inches, a wing tip extension of 14 inches, a horizontal tail extention of 36 inches, a larger dorsal fin and strengthened stabilizer.737-300与737-200具有相同的基本设计，机体伸长了104英寸，翼尖延伸了14英寸，水平尾翼延伸了36英寸，还多了个大的脊鳍和增

9、强的水平尾翼。(8) The 737-400, relative to the 737-300, has body stretch of 120 inches, tow additional overwing exit, tail skid, and strengthened landing gear. 737-400与737-300相比较，机身伸长了120英寸，多了两个逃生出口，尾部滑轨及加强了起落架。(9) The 737-500 uses the 737-300 basic structure with a 94 inches shorter body and a revised for

10、ward and aft fairing (wing to body).737-500使用了737-300的基本结构，机身短了94英寸，并且修改了前后整流罩（机翼到机体）。LESSON 2 THE PNEUMATICS SYSYTEM 增压系统 一、生词目的 环境 发动机引气 接头 防冰 饮用水 在之内 满足 图形 管道 管理、调整Purpose Environment Engine bleed Connector Anti-icing Potable water Within Meet Figure Duct govern压缩空气 阶段，相位 外部的 整流罩 也，此外 液压的 正常的 需要，

11、要求 绝缘 结合、连接 适当的compressure Air 压缩空气 Phase External Cowl Also Hydraulic Normal Need Isolation Join appropriate得到 车 热的 提供 启动器 取代 上部、顶部 活门 交叉、跨接pneumatic Obtain Cart Thermal provide Starter Substitute Top Valve crossover二、TEXT(1) the purpose of the pneumatic sysytem is to supply compressed air for acon

12、trolled temperature and pressure environment during all phases of flight and ground operation .air is obtained from engine bleeds. APU、or from an extermal ground cart through a connector located on the fuselage. 增压系统的作用是为飞行及地面所有阶段的温度和压力控制提供压缩空气。压缩空气的来源可以是发动机引气、APU、或通过机身上的连接头与地面气源车相连供气。(2) The pneuma

13、tic system controls the temperature and the pressure of enginebleed air source. The pneumatic system provides high temperature, high pressure air for the air conditioning .pressurization, wing and cowl thermal anti-icing .also, the pneumatic system provides pressure for the potable water system, hyd

14、raulic system and engine starters. The engine bleed air systems are located on the engine and within the support strut. 增压引气控制发动机引气的温度和压力。增压系统为空调、增压系统、机翼及整流罩热防冰系统提供高温、高压引气。同时，增压系统还给饮用水系统、液压系统和发动机起动系统提供压力。发动机引气系统位于支架内部发动机上。(3) The normal cabin air source is obtained from the 5th-stage of the enginesa

15、t low engine power, 9th-stage air automatically substitutes to meet user system needs.正常情况下，客舱空气来自于发动机低能量的第5级，9级空气自动分配以满足用户系统的需要。(4) On the top of figure 2-1, the isolation valve separates the left and righthalves of the system. On the left side of the isolation valve, the APU bleed air duct joins t

16、he left side crossover duct; on the right side ,the pneumatic ground service connector joins the right side crossover duct. From these ducts the user system are supplied with pressurized air ,governed by the appropriate control valves.在图2-1的上方，隔离活门将左右系统分隔成独立的两部分。在隔离活门的左边，APU引气管道立连接着左交输管道；在右边，压缩空气地面接

17、头连接右交输管道。用户系统可以从这些管道获得压缩空气，通过适当的控制活门进行控制。LESSON 3 AIR CONDINTION空调系统一、单词 空气调节加热 Air conditioning heat 环境 冷却 Ambient Cool 机组 增压 Crew pressurization引出，放出 独立的 暖，热 涡轮冷却器 共同的 膨胀V 零下Bled indenpendent WormAir cycle machine Common Expand Sub-zero总管道 冷却组件 减少 整的 轴 膨胀N 分配 混合 头顶上 防护罩 再分配Manifold Cooling pack Re

18、duce Integral Shaft Expansion Distribute Mix Overhead Shroud Redistribute分离 调节，管理 期望 包括 离开 下降 此外 室、容器 竖管 过滤器 二等分Seprate regulate Desire Consist of Leave Drop In addition Chamber Raise Filter halve配平空气管道 Trim air line 加上，增加 收集器 排出口Add Collector discharge二、TEXT(1) the air conditioning system provides

19、a conditioned air environment for the passengers and crew , heats the cargo compartment, cools the electronic equipment, and supplies air for the pressurization system.空调系统为旅客和机组提供环境温度的控制，为客舱供热，为电子设备舱降温，还有为增压系统提供空气。(2) Air is bled from the pneumatic manifold and conditioned by 2 separate and indepen

20、dent cooling packs. Air flow into the packs is regulated by the pack valves.空气从增压主管道和空调中通过2个隔离的，相互独立的冷却组件中被引入。空气流进组件中通过组件活门调节。(3) Air from the pneumatic manifold is too warm and must be cooled. The pupose of 2 packs is to reduce engine bleed air temperature to the desired temperature.从增压主管道中来的空气太热，需

21、要降温。两个组件的作用就是将发动机引气温度降低到需要的温度。(4) An air cycle machine is an integral unit of each cooling pack. The air cycle machine consists of a turbine wheel and a compressor wheel mounted on a common shaft. Air flowing through the air cycle machine drives the turbine, the turbine drives the compressor section

22、. As the airleaves the turbine it expands greatly. This expansion can cause the temperature of the air to drop to sub-zero levels.涡轮冷却器是构成每个冷却组件所必需的。它包括一个涡轮和一个压气机，安装在共同的轴上。气流通过涡轮冷却器驱动涡轮，涡轮驱动压气机部分。当空气离开涡轮后急剧膨胀。这种膨胀能够导致空气温度降到零度以下的程度。(5) In figure 3-1, we can see that the conditioned air from the right

23、 pack flows into the main distribution manifold, the conditioned air from the left pack flows into the main distribution manifold and into the flight compartment. In addition, a trim air line from the left mix chamber adds hot air to the flight compartment duct. The main distribution manifold suppli

24、es the passenger compartment overhead distribution system through tow sidewall risers.在图3-1中，我们可以看出，调节空气从右组件流向主分配管道，还有调节空气从左组件流向主分配管道和进入驾驶舱。另外，从左混合舱出来的配平空气管道增加热空气给驾驶舱管道。主分配管道通过两个侧壁竖管供气给客舱顶部分配系统。(6) A 3-phase fan draws air from the collector shroud through filters and discharges into the main distrib

25、ution manifold for redistribution. 一个三相风扇从收集器防护罩穿过过；滤器和排出口进入主分配管道，用以再分配。LESSON 4 PRESSURIZATION INTRODUCTION增压系统简介 一、单词组件 外流阀 目的地 曲线 巡航 爬升Pack Outflow valve destination Curve Curise Ascend控制 保持 安全的 对时间的 虚线 下降Control Maintain Safe Against time Dotted line Descent座舱高度Cabin altitude尽可能的 As as possible

26、舒适的 起飞 实线 近Comfortable Takeoff Solid line Near环境 ambient 减小 大气 per 参照decrease Atmosphere By referring变化率 例子 图表 称之为 毫巴 排出rate Example ChartIs referred to as Millibar exhaust确定、决定 Determine 磅/英寸 描绘 制度 相等的 向机舱外Psi=pound square inch Depict Sytstem identical outbroud与的关系曲线 versus 水银 施加mercury exert二、TEXT

27、(1) the air conditioning packs supply conditioned air into pressurization system. the pressurization system controls cabin altitude by regulating air flow from the fuselage, through the outflow valve. The pressurization system maintains cabin altitude as close to sea level as possible or at an altit

28、ude equal to the altitude of the flight destination, so the pressurization system provides a safe comfortable cabin altitude for the crew and passenger at all airplane altitude.空调组件为增压系统提供调节空气。增压系统通过调节机身气流控制客舱高度，通过外流阀，增压系统保持客舱高度尽可能的接近海平面或等于飞行目的地高度，这样增压系统可为机组和旅客在整个飞行过程中提供一个安全舒适的客舱高度。(2) Figure 4-2 sh

29、ows a curve of airplane and cabin altitude against time from take off through cruise to landing .airplane altitude is shown in dotted line. Cabin altitude is shown in solid line. The airplane starts its flight at an airport altitude near sea level, ascends, cruises, and descends to a landing airport

30、 near sea level.图4-2显示为飞机和坐舱高度在起飞、巡航及着陆阶段的时间曲线。飞机高度显示为虚线，坐舱高度显示为实线。飞机以接近海平面的机场高度开始飞行、爬升、巡航、下降和接近海平面的机场着陆。 (3) Cabin altitude starts at the take off altitude. As the airplane climb, the ambient pressure decreases; the higher the altitude, the lower the pressure. The altitude inside the airplane (cabi

31、n altitude)also climbs but at a lowerrate than the airplane. The pressurization system provides the pressure differential between the cabin and ambient.客趁高度开始于起飞高度。当飞机爬升时，环境压力减小，高度越高，压力越低。飞机内部高度（坐舱高度）也以一个低于飞机的速率爬升。增压系统提供客舱与外界环境之间的压力差。(4) The airplane altitude above sea level is determined by measuri

32、ng thepressure of the ambient atmosphere. For example, see figure4-3, at 30,000 feet above sea level the ambient pressure would be 4.36 psi. the cabin altitude can be measured by adding the ambient pressure to the 7.80 psid maintained in side the airplane by the pressurization system: ambient pressu

33、re 4.36 psi at 30,000 ft.Pressuree diffeential 7.80psid12.16psiby referring to the chart depicting ambient pressure versus altitude, if the ambient pressure is 12.16psi, the cabin altitude would be 5150 ft (see sigure 4-3).飞机高度可通过测量环境大气的压力来测得。例如：图4-3，在高于海平面3万英尺的环境压力为4.36PSI。客舱高度可通过环境压力加7.8PSID来测得，7.

34、8PSID由增压系统保持：环境压力：4.36PSI 30000FT压力差；7.8PSID坐舱压力：4.36+7.8=12.16PSID参照图表描述环境压力高度曲线，如果环境压力是12.16PSID，客舱 高度将是5150英尺（图4-3）(5) the cabin pressure is referred to as “psid” and indicates the differential pressure, in pounds per square inch , between inside and outside of the airplane. There are many system

35、s for measuring pressure and “psi” is only one .airplane systems measure pressure in inches of mercury and millibars; these indications are identical to 14.7psi as a measurement of the pressureexerted by the atmosphere at sea level.客舱压力被称为“PSID”并用“磅/英尺”指出压力差，在飞机内外，有许多系统可测量压力，“PSI”只是其中之一。飞机系统用英寸水银或毫巴

36、来测量压力；这些指示等同于受到海平面大气压力14.7PSI。 (6) The pressure control systems provide cabin differential pressure by controlling the outflow of air from the faselage. The pressure control system consists of an aft outflow valve, forward outflow valve, pressure controller, control panel, pressure sensing inputs, a

37、nd monitoring indicators.压力控制系统通过控制机外气流来提供客舱压力差。压力控制系统包括一个外流阀、前外流阀、压力控制器、控制面板、压力传感器和监视器。(7) The aft outflow valve allowing cabin air to exhaust overboard to maintain cabin pressure. The forward outflow valve receives a control signal from the aft outflow valve . when the aft outflow valve is closed,

38、 the forward outflow valve receives a signal to drive full closed.后外流阀允许客舱空气排出到机外以保持客舱压力。前外流阀接收一个从后外流阀来的控制信号。当后外流阀被关闭时，前外流阀接收又个信号驱使完全关闭。LESSON 5 FIRE DETECTION火警探测 一、单词火警探测 监控 部件 过热 发生 面板 机翼 厕所 可选的Fire detection Monitor Component Overheat Occur Panel Wing Lavatory optional在周围 存在 警告 铃声 听觉 器件 灭火器 瓶 角落

39、Around Exist Alarm Bell Aural device Extinguish Bottle Corner组件 泄漏 报警器 规定 在之下Pack Leak horn specify beneath与相对应 Respond to 盆basin擦手纸斜槽 Tower chute特征 可用的 位置 元件feature Available Location element轮子 放出 完成 天花板wheel discharge Accomplish Ceiling二、TEXT(1) the fire detection systems monitor airplane componen

40、ts for overheat, fire or smoke condition. Engine and APU fire and overheat indication occurs on the P8 and P7 panels. Wing and body duct overheat warning occurs on the P5 and P7 panels. Lavatory smoke detection indication is an optional feature that is available. Indication can occur at the lavatory

41、 location and or on the P5 panel.火警探测系统监控飞机组件的过热、失火或烟雾等情况。发动机和APU过热和失火指示出现在P8或P7板上。机翼和机身管道过热警告出现在P5或P7板上。厕所烟雾探测指示是一个可选装配件。指示能够出现在厕所位置或P5板上。(2) Engine fire and overheat detection is provided by detector elements located around the engine. The engine and APU fire detection accessory unit M279, located

42、 in the E/E bay determines if a fire or overheat condition exists. When detected indications occur in the flight deck an alarm bell is provided by the aural warning devices unit M315 for a fire condition. The two engine fire extinguisher bottles are located on the upper left aft corner of the main w

43、heel well and are discharged from the flight deck.发动机失火和过热信号探测由安装在发动机周围的探测元件提供。发动机和APU火警探测组件M279，安装在电子设备舱，用于判断是否有失火或过热情况发生。当在飞机蒙皮探测到火警信号时，音响警告设备M315将给出一个警告铃声。两台发动机灭火瓶安装在主轮舱左下方后角处，并从处释放。(3) The APU detectors sense fire conditions only. Monitoring of the sensors is accomplished by the M279. indication

44、s occur on the P28 panel in thewheel well and also in the flight deck. The APU fire bottle is located behind the aft pressure bulkhead and is discharged either from the flight deck or P28 panel.APU探测器只感应火警信号。传感器的监控由M279完成。指示出现在P28板在主轮舱和FLIGHT DECK。 APU灭火瓶后压力隔板上，并通过P28板或FLIGH DECK释放。(4) Wheel well fi

45、re detection is provided by detector elements mounted on the wheel well ceiling. The detectors provide input to the M237 module located in the E/E bay. Indications occur on the P7 and P8 panels and an alarm bell is provided by the M315 module.轮舱火警探测由安装在轮舱天花板上的探测元件来提供。探测器提供信号给安装在电子设备舱的M237组件。指示信号出现在P

46、7和P8板上，警告铃声由M315组件提供。(5) The wing and body overheat detection system exists to monitor thepneumatic system for leaks . the detection system is divided into a left and right system. The detectors provide input to the M237 module. Overheat indication occurs on the P5 and P7 panels.机翼和机身过热探测系统监控增压系统有无渗

47、漏。探测系统分为左右两部分。探测器提供信号给M237组件。过热指示信号出现在P5和P7板上。(6) The lavatory smoke detector is located in each lavatory, the detector will provide a warning horn and indication at a specified smoke level .located in each lavatory, beneath the wash basin, is a fire extinguisher bottle which responds to high temper

48、ature in the tower chute.厕所烟雾探测器安装在每个厕所里，探测器将在规定的烟雾层度发出警告信号。灭火瓶安装在每个厕所，洗手池下面，可以对擦手纸斜槽里的高温情况作出响应。LESSON 6 OXYGEN SYSTEM氧气系统 一、单词氧气 安装 稀释器 服务员 面罩 压强计 紧急情况 作动筒 自动地Oxygen Install Diluter Attandent Mask Gage Emergence Actuator automatically要求、命令 气态的 要求 气缸 切断 即使 锁定 机构 人工地Acquire Gaseous Demand Cylinder Sh

49、ut off In a event of Latch Mechanism manually单独的 称为 化学上 旅客服务设备 数量 排出 释放independent designate Chemically Passengers service unit Quantity Vent Release开动，启动 activate二、TEXT(1) the purpose of the oxygen system is to provide oxygen for the flight crew and passengers when required. Two independent oxygen

50、system are installed in B737. the flight crew oxygen system is a high pressure gaseous system for flight crew use only, this type of system is designated a “diluter demand” system . The passenger oxygen system is a chemically-generated oxygen system for use by passengers and cabin attendants. This t

51、ype of system is designated a “continuous flow” system. 氧气系统用来为机组及旅客提供氧气。B737上安装有两套氧气系统。机组氧气系统是一个仅供机组使用的高压气态系统，这种系统被称为“稀释要求”系统。旅客氧气系统是一供旅客及乘务员使用个化学制氧系统。这种系统被称为“continuous flow”系统。(2) The flight crew oxygen system consists of an oxygen cylinder. Valves, indicating components, distribution tubing and

52、oxygen mask/regulator. The crew oxygen system components are located in the forward cargo compartment and in the flight compartment.机组氧气系统包括一个氧气瓶，阀门，指示组件，分配管道及氧气面罩/调节器。机组氧气系统组件安装在前客舱和驾驶舱内。 (3) Oxygen flows through the pressure reducing regulator and shut off valveto the masks. Quantity (pressure) in

53、dication is provided by a gage in the flight compartment. In the event of an overpressure, the cylinder is vented to ambient through the overboard discharge. The cylinder is serviced after removal from the aircraft.氧气通过减压调节器和关断活门流向氧气面罩。流量指示由驾驶舱内的压强计指示。一旦过压，气瓶将通过顶部释放开关进行释压。气瓶应从飞机上取下进行勤务。(4) The passe

54、nger oxygen system provides an emergency oxygen supply to the passengers and attendants, this system consists of passenger sevice units, control and indication. This service units contain the mask box, door latch release actuator, latching mechanism, chemical oxygen generator and oxygen mask.旅客氧气系统为

55、旅客及乘务员提供应急氧气，系统包括旅客服务设备，控制及指示器。这个服务设备包括氧气面罩盒、门锁释放作动筒，锁定机械装置、氧气发生器及氧气面罩。(5) The passenger oxygen system can be activated automatically by high cabin altitude (low cabin pressure) or manually from the flight compartment.旅客氧气系统能够被较高的客舱高度自动启动，也能在驾驶舱人工启动。LESSON 7 ICE AND RAIN PROTECTION防冰、防雨 一、单词雨Rain保护

56、雨刷 卫生间 皮托静压 支柱管 强度 涂层Protect Wiper Toilet Pitot static Mast Strengthen coating帮助 防雨剂 排放 探头 堆积 雾 暴露Aid Repellent Drain Probe Buildup Fog expose为而提供 Is provided for 叶片 视线 迎角叶片 碰撞 导电的Vane Vision Alpha vane Impact conductive气流 原因 槽 装置Airstream Cause Sink fitting形成 出故障的 嵌入Formatting Faulty Embed with结冰 损

57、失 垫圈Freeze Loss gasket与结合在一起 Are integrated二、TEXT(1) the ice and rain protection system protects the airplane and aids the flight crew when operating under ice and rain conditions. Ice and rain protection is provided for:1) wing leading edge slats outboard of each engine. 2) Flight compartment windo

58、ws (heat, wiper, rain repellent). 3) Pitot static and temperature probes. 4) Alpha vanes. 5) Toilet drains.防冰、防雨系统用于保护飞机及帮助机组在雨雪天气下操作飞机。此系统为下列部件提供保护： 1） 发动机外前缘缝翼；2） 驾驶舱玻璃窗（加热、雨刷、防雨剂）； 3） 皮托静压管及总温探头； 4） 迎角叶片； 5） 厕所排水。(2) Wing leading slats use hot air from the pneumatic system. Flight compartment windows are electrically heated. The wipers and rain repellent are used for providing clear vision. The pitot static probes, alpha vanes, drain masts, and toilet drains use electric heaters.前缘缝翼用增压系统的热引气加温。