专业资料
航空工程英语
Application of 28 volt dc to trip. Reverses the polarity of the coil and the contactor opens assisted by the spring. The coil deenergizes through the auxiliary contact.
28伏直流电关闭的应用，允许线圈瞬时接通。当跳开关闭合时，线圈通过辅助触点断电，跳开关通过永久磁铁被保持在闭合位。28伏直流电松开的应用，将线圈极性反向，触点在弹簧的帮助下打开。线圈通过辅助触点断电。 6. The 115 volt ac, 400HZ, 3-pahse power from an external source (ground power unit ) can also be supplied to the airplane for systems use. The external ac power system consists of an external power receptacle, bus protection panel, two external power contactors, relays, switches and indicating lights. The ac external power receptacle is located on the right side of the airplane, forward of the nose wheel well, the bus protection panel (BPP) is used for control and protection of the airplane circuits connected to external power. The two external power contactors connect 115 volt ac, 400Hertz, 3-phase power to the distribution system from external power source.
从外部电源的（地面电源）400HZ，115伏三相交流电也能够提供到飞机上供系统使用。外部交流电源系统包括一个外部电源插座，汇流条防换板，两个外部电源接触器、继电器、开关及指示灯。外部交流电源插座位于飞机右侧、前轮舱前方。汇流条防护板用来保护与外部电源连接的飞机线路。两个接触器将外部来的115伏，400HZ的三相交流电源接到分配系统。 7. The 115 volt ac system is supplied by two engine driven generators, APU driven generator or external power. The powr is connected to the generator main busses by engine generator breakers. APU breakers and external power contactors. Power is also supplied to two transfer busses through transfer relays. External power can be supplied to the external ac bus and the ground service bus (this bus is used for servicing of the airplane). The ground service bus can also be supplied from generator bus NO.1.
115伏交流电源由两台发动机驱动的发电机、APU发电机或地面电源提供。它被发动机跳开关、APU跳开关或地面电源触点连接到发电机主汇流条上，它也可以通过转换继电器接到两个转换汇流条上。外部电源也能够供到外部交流汇流条及地面服务汇流条上。地面服务汇流条也能够从一号发电机汇流条供电。 8. The 28 volt ac system is obtained through transrformers from main, transfer ,and ground service busses. The 28 volt dc power is supplied from the battery and transformer rectifiers to the battery bus and two dc busses. The power is connected to the busses by relays. The battery charger is supplied with power from the 115 volt ac system. The electronic system power is supplied from the 115 volt ac and 28 volt dc system. The standby ac and dc busses are powered normally from the generated ac and dc power. Alternately, the battery supplies power to the standby system. The standby power components are located in the electronics compartment, P6 panel and p5 panel .the purpose of the standby power distribution is to provide 115 volt ac and 28 volt dc power to essential system during absence of normal supply. 通过转换主汇流条、转换汇流条或地面服务汇流条上的电源可得到28伏交流电。28伏直流电由电瓶及转换整流器到电瓶汇流条和两个直流汇流条。28伏直流电被继电器接到这个汇流条上。电瓶充电器由115伏交流电供电。电源系统由115伏交流和28伏直流电提供。备用交流和直流电由正常交流和直流电提供。另一方面，电瓶为备用系统提供电源。备用电源组件位于电子舱、P5及P6面板。备用电源分配的目的是在无法正常供电的期间为必要系统提供115伏交流电或28伏直流电。
LESSON 20 NAVIGATION 导航
一、单词 导航 包含 Navigation Include 计算 子系统 Compute Subsystem 运动 自动定向仪 Movement Automatic director finder 相对方位 Relative bearing 甚高频全向信标 Magnetic bearing 偏离 Turn 最佳的 Very high frequency 仪表着陆系统 Instrument landing omnirange system Optimum 航线 测距仪 Course Distance measure equipment Identification Pitot pressure 磁方位角 转动 斜距 高度 静压 Slant range Altitude Static pressure 空中交通管制 Air traffic control 识别 大气数据系统 Air data system 不同的 Various 全压 惯性基准系统 Inertial reference system 姿态 气象雷达 Attitude Weather radar 关键的 当前位置 Key Present position 航向 电子飞行仪表系统 低空无线电高度表 Hearing Electronic flight instrument system Low range radio altimeter 地图 Map 绝对的 Absolute 26
专业资料
航空工程英语
Height 近地警告系统 Ground proximity warning system 不安全的 Unsafe 听觉 Aural 高度 视觉的 Visual 飞行管理计算机系统 指点标 起源 Flight management computer system Maker beacon Origin 领航 特殊的 Navigate Specific 最佳的 Optimization 以前 到来 大圆弧 可能的 计算 适合于 远距离的 爬高 previously advent Great circle Possible Computation Suit Distant Climb 终点 直接 destination Direct 随着?出现 With the advent of 强烈期望的 误差 冗长 机载的 复杂的 Highly desirable Error Lengthy Onboard Complex 有可能的 核实 耗费 附近的 最佳的 potential verify Comsume Nearby Optimize 剖面 计划 profile Projection 预测 分段爬升 下降 利用 predict Step climb Descent Utilization 更进一步 巡航 贯穿 综合飞行系统附件装置 further Cruise Throughout Integrated flight system accessory unit Test Failure 以及 As well as 把?做为目标 Target 航线可更换件 Line replaceable unit 印刷电路板 数模适配器 Print circuit card 试验 Data analog adapter Status 故障 抑制 存储器 suppression Memory 状态 航空无线电公司 自检测设备 Aeronautical radio 数据总线 incorporated Build –in text equipment Data bus 无线电距离磁Radio distance 指示器 magnetic indicator 离散的 discrete 完成 perform 任务 Task 燃油累加装置 Fuel summation unit 飞行控制计算Flight control 机 computer 2. TEXT 1. the navigation system compute and display the airplane’s position and movement over the earth’s surface. The navigation systems include the following main subsystems:
ADF automatic direction finder — ADF system provide a display of the relative bearing ?
to a selected ground transmitter.
VOR/ILS(very high frequency omnirange/instrument landing system)— this system provide ?
displays of relative and magnetic bearing to a selected VOR station and deviation from a preselected course. When truned to an ILS frequency, the system provides a display of the lateral and vertical deviation from the optimum landing path.
DOM(distance measuring equipment) —DME system measures the slant range distance to the ?
selected DME facility.
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专业资料
航空工程英语
ATC (air traffic control)— ATC system transmits airplane identification and altitude ?
data to a ground facility.
ADS (air data system)— ADS system measures pitot and static pressure and total air ?
temperature and computes various air data parameters.
IRS(inertial reference system)— this system provides outputs of key navigation ?
parameters such as heading, attitude, and airplane present position.
EFIS(electronic flight instrument system )— this system providesdisplays of ?
information from various airplane systems.
WXR(weather radar) —this system provides a display of the weather conditions forward ?
of the airplane, and can also provide a map display.
LRRA(low range radio altimeter)— this system measures the absolute height of the ?
airplane above the earth’s surface.
GPWS(ground proximity warning system)— this system uses inputs from other systems to ?
navigatee the airplane and provide optimization of the flight plan.
FMCS(flight management computer system)— this system provides the pitot with aural and ?
visual warning of an unsafe flight path relative to the earth’s surface.
MKR BCN(marker beacon ) —this system provides an indication when the airpnale is passing ?
over a specific position.
TCAS(traffic alert and collision avoidance system)— this system provides the pitots ?
with warnings and advisories of unsafe flight conditions with regard to other airplanes operating in the area.
导航系统计算并显示飞机的位置及其在地球表面的移动。导航系统包括下列子系统： ?
自动定向机——此系统提供一个相对一个选定的地面发射台的相对方位角显示。 ?
甚高频全向信标/仪表着陆系统——此系统提供飞机相对于一个选定的VOR台的磁方位及飞机与?
预选航道的偏离显示信号。当转动仪表着陆系统的频率时，此系统显示飞机与最佳着陆路径在水平及垂直方向上的偏差。
测距机—— 此系统用来测量飞机与选定的DME设备的斜距。 ?
空中交通管制—— 此系统发射飞机识别码及高度信号给地面设备。 ?
大气数据系统—— 此系统测量皮托管压力、静压及空气总温并计算出不同的大气数据参数。 ?
惯性基准系统—— 此系统输出例如像航向、高度及飞机当前位置等关键导航参数。 ?
电子飞行仪表系统—— 此系统提供飞机各系统不同系统的显示。 ?
气象雷达—— 此系统提供飞机前方气象状况的显示，并能进行地图显示。 ?
低空无线电高度表—— 此系统测量飞机与地球表面的绝对高度。 ?
近地警告系统—— 此系统通过其它系统的输入引导飞机并提供最佳参数选定的飞行计划。 ?
飞行管理计算机系统—— 此系统用音响或视觉警告给飞行员相对于地球表面不安全的飞行路?
径。
指点信标—— 此系统提供当飞机飞经一个特定的位置时进行指示。 ?
警告及防撞系统—— 此系统为飞行员提供在此区域内相对于其它飞机处在不安全的情况下提?
供警告及建议。 2. Previously, airplanes were navigated by flying from station to station along the route from the airplane’s origin to destination. The pitot used distance measuring equipment(DME), VHF omnirange (VOR)and automatic direction finder(ADF) to fly to each station. With the advent of inertial navigation system(INS), it became possible to fly a more direct route from origin to destinatin. A direct, great circle route is highly desirable because of potential fuel and time savings. Because of possible position errors in inertial systems the pitot is required to verify the inertial position with the DOME, VOR and ADF system. The computations required to verify the inertial position are lengthy and time consuming and are much more suited to an onboard computer. Also, since the airplane is not on a course to a nearby station but on a direct course to a distant destination, the computations are move complex. 3. The flight management computer system (FMCS) continuously calculates the optimum flight path and engine thrust to save time and fuel. During takeoff, the FMCS provides optimized thrust setting for takeoff based on gross weight of the airplane and outside temperature. During climb, the FMCS provides optimized climb profiles by predicting both opimum altitude and cruise speeds.further, the FMCS provides projections of top of climb and step climbs. During cruise, the FMCS optimizes descents by predicting top of descent speeds are targeted to make maximum utilization of the potential energy of the airplane.
飞行管理计算机系统继续计算最佳的飞行路径及发动机推力，以节省时间和燃油。在起飞期间，飞行管理计算机系统依据飞机总重及外界温度为飞机起飞提供最佳的推力设置。在爬升阶段，飞行管理计算机系统通过预测最佳姿态及巡航速度来提供最佳的爬升剖面。更进一步的，飞行管理计算机系统提供爬升到顶的计划及分段爬升。在巡航阶段，飞行管理计算机系统在导航数据的基础上通过预测下降顶端来优化下降。在整个下降阶段，下降速度是 4. There are two important equipment used in navigation system, one is the integrated flight systems accessory unit (IFSAU), the other is the digital to analog adapter(DAA). This IFSAU is line replaceable unit (LRU) located in the electronic equipment compartment. Is contains two printed circuit card(A1,A2). Each of the cards is connected to a different rear connector on the LRU. The A1 card is the IFSAU autopilot card, it has cirnce system(IRS). It stores inflight failures of the IRS in memory and monitors the IRS for current status.
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专业资料
航空工程英语
THE DAA converts the ARINC 429 data bus output from the IRS into an analog format and sends that data to the radio distance magnetic indicator9RDMI). The DAA converts an IRS BITE request discrete from the flight management computer system into an analog signal and sends it to the IRS. 6. The DAA perform other tasks not related with the IRS. They convert VOR/ILS navigation system signals from analog format into ARINC 429 format and sent the data to the electronic flight instrument system (EFIS) for display to the flight crew. The DAA convert analog information from the fuel summation unit into data information and send the information on an ARINC 429 data bus to the FMCS. The DAA also converts the low speed N1 from ARINC 429 format into analog format and sends the N1 information to the engine indicator. The DAA alos converts DME distance from ARINC 568 to ARINC 429 and sends it to the flight control computer(FCC) and the electronic flight instrument system (EFIS).
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