航空电子设备
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作者何晓薇,向淑兰 编
出版社西南交通大学出版社
ISBN9787564352035
出版时间2017-01
装帧平装
开本16开
定价38元
货号1201483625
上书时间2024-11-20
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目录
Chapter 1 Air Data Computer System
1. 1 Introduction
1.2 The Basic Principle
1.3 Temperature Measurement Probes
1.4 Pressure Transducers
1.5 Air Data Instruments
Chapter 2 Electronic Instrument Systems
2.1 Introduction
2.2 Electronic Flight Instrument Systems
2.3 Engine Indicating and Crew Alerting System
2.4 Electronic Centralized Aircraft Monitoring
Chapter 3 Automatic Flight Control Systems
3.1 Introduction
3.2 The Flight Director
3.3 The Autopilot
3.4 Autopilot Flight Director Systems
3.5 The Yaw Damper
3.6 Automatic Pitch Trim
3.7 Autothrottle
3.8 Autoland
3.9 Flight Envelope Protection
3.10 Typical Auto Flight Operation for B767 Airplane
Chapter 4 Flight Data Recording & Airplane Condition Monitoring System
4.1 Introduction
4.2 Flight Data Recording System
4.3 Airplane Condition Monitoring System
Chapter 5 Airborne Weather Radar System
5.1 Introduction
5.2 Basic Principles
5.3 Control Panel
5.4 Display-EHSI Presentation
5.5 Operation In-Flight
5.6 Warning
Chapter 6 Secondary Surveillance Radar and Transponder
6.1 Introduction
6.2 Air Traffic Control Radar Beacon System
6.3 Mode S Secondary Radar System
Chapter 7 Traffic Alert and Collision Avoidance System
7.1 Introduction
7.2 TCAS II System Architecture
7.3 The Principle of Operation of TCAS II
7.4 TCAS II Displays
7.5 TCAS II Aural Messages
7.6 Control Panel
7.7 Crew Response
7.8 The Use of TCAS II
7.9 Flight Crew Procedure for A320 Airplane
Chapter 8 Ground Proximity Warning System
8.1 Introduction
8.2 GPWS System Architecture
8.3 GPWS Alert Modes
Chapter 9 Enhanced Ground Proximity Warning System
9.1 Introduction
9.2 Enhanced GPWS Features
9.3 Look-Ahead Terrain Alerting
9.4 Terrain Display
9.5 Flight Deck Effects for EGPWS Alert
9.6 Aural Message Priority
9.7 EGPWS Control Panel
9.8 Flight Crew Procedures
Chapter 10 Runway Awareness and Advisory System
10.1 Introduction
10.2 The Principle of RAAS
10.3 System Operation Description
10.4 RAAS Quick Reference
Chapter 11 Predictive Windshear System
11.1 Introduction
11.2 The Principle of PWS
11.3 Limitations of PWS
11.4 The Alert of PWS
11.5 The Operation of PWS
11.6 Flight Crew Procedure for A320 Airplane
Chapter 12 Radio Altimeter
12.1 Introduction
12.2 The Principle of LRRA
12.3 Radio Altitude Display
12.4 Errors and Accuracy
Chapter 13 Inertial Navigation System
13.1 Introduction
13.2 The Principle and Construction of the Accelerometer
13.3 The Gyro-Stabilised (Gimballed) Platform
13.4 Position Calculation
13.5 INS Self-Alignment
13.6 INS Error Corrections
13.7 Mode Selector Panel and CDU
Chapter 14 Inertial Reference System
14.1 Description of the Strapdown System
14.2 The Control and Display oflRS
14.3 The IRS Outputs
14.4 IRS Alignment
Chapter 15 Global Positioning System
15.1 Introduction
15.2 GPS Elements
15.3 GPS Operating Principle
15.4 GPS Receiver Unit
15.5 GPS Reliability/Integrity
15.6 GPS Errors
15.7 Differential GPS
Chapter 16 Flight Management Computer System
16.1 Introduction
16.2 FMCS Architecture
16.3 Command Display Unit
16.4 The Flight Management Computer Database
16.5 General FMS Operation
References
内容摘要
本书是航空电子设备英文版，系统介绍了民航当前采用的通信、导航、仪表及自动控制系统的种类、功能和工作原理，包括：高频通信、甚高频通信等常见机载通信设备的原理、结构、使用方法，四大导航设备(VOR、DME、ILS和ADF)、雷达系统及机载监视设备(TCAS、GPWS和风切变探测系统)等的原理与使用方法， 航空仪表的基础知识和飞机的基本仪表设备，自动飞行控制系统的作用、组成、控制规律等。
精彩内容
Chapter 1 Air Data Computer System
1.1 Introduction
Many of the primary flight instruments on an aeroplane are dependent on pressures transmitted from the pitot/static probes through a system of pipelines before reaching the sensors in the instruments.Larger aeroplanes require longer pipes,which results in increased lag errors and greater risk of breakage/leakage.To overcome these,and to create other benefits,most modern transport category aeroplanes use Air Data Computers (ADC).
Air data computers are usually of the digital type;that is,they transmit data in digital format which is compatible with other computer-based systems.Analogue air data computers,which transmit their output data to servo-operated devices,are less common,although a few are still in existence.
1.2 The Basic Principle
The ADC takes inputs from the pilot and static pressure sources,converts them to electrical signals,and then transmits them via a data bus to the various flight instruments.In addition,input from the outside air temperature probe is used to calculate the true airspeed.In some later models of ADC,the angle of attack (alpha) sensor inputs are also provided.Normally there will be two ADCs to provide redundancy,each pilot is able to switch to the output of the other ADC.See Figure 1.1.
Figure 1.2 is a block diagram showing the data inputs and outputs of a typical ADC.Output signals are transmitted as electronic data to operate the pilots' air data instrument displays,plus TAS,TAT and SAT (static air temperature) displays.
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