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
摘要
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.
