Chapter 2 Aircraft Systems...Advanced Course of Aerospace Guidance and Control Chapter I-2 Aircraft...
Transcript of Chapter 2 Aircraft Systems...Advanced Course of Aerospace Guidance and Control Chapter I-2 Aircraft...
Advanced Course of Aerospace Guidance and Control Chapter I-2 Aircraft Systems
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Chapter 2 Aircraft Systems
Boeing747
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Boeing747-400
Aircraft Dimensions
TypeIssue
Wing Span (m)
Length (m)
Height (m)
Passengers (-)
Maximum Take Off Weight (kg)
Maximum Landing Weight (kg)
Maximum Zero Fuel Weight (kg)
Maximum Payload Weight (kg)
Maximum Fuel Weight (kg)
Maximum Operational Altitude (km)
Maximum Operational Speed (km/h)
Cruise Speed (km/h)
Cruise Time (h)
Flight Range (km)
Take Off Distance (m)
Landing Distance (m)
Engine
Engine
Manufacturer
General Electric
Thrust
Boeing
Advanced Course of Aerospace Guidance and Control Chapter I-2 Aircraft Systems
2.1 Aerodynamic Control Surfaces
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Control Function Aerodynamic Surfaces
Primary
Control
Pitch Control
■Inboard Elevator
■IOutboard Elevator
■Variable-incidence
Horizontal Stabilizer
Roll Control
■Inboard Aileron
■Outboard Aileron
■Inboard Spoiler
■Outboard Spoiler
Yaw Control■Upper Rudder
■Lower Rudder
Secondary
Control Sy
High Lift Device
■Kruger Flap
■Variable-Camber
Leading Edge Flap
■Inboard Flap
■Outboard Flap
Ground Speed
Brake
■Inboard Spoiler
■Outboard Spoiler
Ground Spoiler
Flight Spoiler
Inboard Aileron
Triple Slotted Flap
High Speed Aileron
Low Speed Aileron
Outboard Flap
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Pitching Control by Elevator
Elevator
+YB
XB
ZB
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Rolling Control by Aileron
Aileron
+
+
YB
XB
ZB
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Yawing Control by Rudder
Rudder
+
YB
XB
ZB
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Mechanical Control System
(Irreversible)
Elevator Control System
Mechanical Cable
Control Wheel
Right
Inboard
Elevator
Right Outboard Elevator
Left Inboard Elevator
Right Outboard Elevator
Mechanical Control Unit
(Pneumatic Sys. No.1 & No.2)
Mechanical Control Unit
(Pneumatic Sys. No.4)
Angle Sensor
Mechanical Control Unit
(Pneumatic Sys. No.1 & No.2)
Mechanical Control Unit
(Pneumatic Sys. No.1) Elevator Cable
Artificial Feel Unit
Pulley
Dynamic Pressure Sensor
Artificial Feel Computer
Elevator Cable
Control
Column
Mechanical Control System (Irreversible)
Bob Weight
Artificial Feel Spring
Pneumatic System
Return
Pressure
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Boeing 747-100Boeing 747-400
Cockpit Evolution
from Analog to Digital
2.2 Flight Management
and Control
Systems
Advanced Course of Aerospace Guidance and Control Chapter I-2 Aircraft Systems
10FMS (Flight Management System)
Pilot Control, Display
Computation System
Control
Surface
ILS: Instrumental Landing
System
MLS: Microwave Landing
System
MCP: Mode Control Panel
ADC: Air Data Computer
INS: Inertia Navigation
System
MCDU: Multi Purpose Display
and Control Unite
EFIS: Electric Flight
Instrument System
Pilot Stick
ILS/ MLS
MCP
ADS/ INS
MCDU
EFIS
Nav. Radio
Throttle
Stick Angle
Approach Path
Control Mode
Target
Velocity Position
Attitude
Flight Plan
Flight Inf.
Direction/ Distance
Lever Angle
Flight Inf.
Flig
ht
Co
ntr
ol
Co
mp
ute
r
Th
rust
Co
ntr
ol
Co
mp
ute
r
Flig
ht
Man
ag
em
en
t C
om
pu
ter
Optimal Velocity
Co
ntr
ol
Su
rfa
ce
Angle
Command
Thrust
Command
En
gin
e
Engine
System
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(Electronic Flight
Instrument
System)
(Electronic Horizontal
Situation Indicator)
(Electronic
Attitude Director
Indicator)
(Engine Indication and
Crew Alerting System)
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Glare Shield
1. FD (Flight Director) Switch 3. EFIS Brightness Control Panel
2. EFIS (Electronic Flight Instrument 4. System Control Panel
System) Control Panel ・A/P (Auto Pilot)
・PDF (Primary Flight Display) ・A/T (Auto Throttle)
・ND (Navigation Display)
Overhead Panel
1. Electric Engine 5. Center Panel (Upper) 10. Anti-Ice 15. ECS (Environmental
Control Panel 6. Fire Panel Panel Control System)
2. IRS (Inertial Reference 7. Engine Start 11. Timer Air Conditioning Panel
System) Panel Panel 12. Cabin Oxygen Panel 16. Bleed Air Panel
3. Power System Panel 8. Fuel Jettisoning Panel 13. Yaw Damper 17. Light Switch Panel
4. Hydraulic System Panel 9. Fuel Panel 14. Cabin Altitude Panel
Main Panel
1. Source Select Panel 7. Ground Proximity Warn. Panel 12. EICAS (Engine Indication 14. RMI (Radio Magnetic
2. Clock 8. Alternate Flap and Crew Alerting System) Indicator)
3. CRT Select Panel and Gear E I U Selector 15. ADI (Attitude Director
4. Flight Number 9. Landing Gear Lever Display Computer Indicator)
Reminder 10. FMC Master Switch 13. Primary EICAS 16. Air Speed Indicator
5. PFD (Primary Flt. Disp.) 11. Heading (Engine Indication and 17. Pressure Altimeter
6. ND (Navigation Display) Reference Switch Crew Alerting System) 18. Brake Pneumatic Meter
Center Pedestal (Center Panel)
1. CDU 4. Parking Brake 8. Flap Lever 13. Weather Radar Panel
(Control Display Unit) Lever 9. Trim Cut-out 14. Trim Panel
2. EICAS (Engine 5. Speed Brake Switch 15. Transponder
Indication and Crew 6. Thrust Lever 10. Radio Panel 16. Auto Brake
Alerting System) ・TO/ GA (Go Around) Switch 11. Audio Panel 17. ACARS Printer
3. Stabilizer Trim Indicator 7. Fuel Control Switch 12. Cabin Signal Panel
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IDS(Integrated Display System)
■EFIS
(Electronic Flight Instrument System)
・PFD(Primary Flight Display)
EADI(Electronic Attitude
Director Indicator)
EHSI(Electronic Horizontal
Situation Indicator)
・ND(Navigation Display)
■EICAS
(Engine Indication Crew Alerting System)
■FMS-CDU
(Flight Management System-Control Display Unit)
IDS(Integrated Display System)
Weather
Radar
Air Data Computer
Anti-Ice Unit
ECS
Door
Landing Gear
Pneumatic Sys.
Flt Cont. Sys.
Radio Nav.
Stall Warn. Comp.
Elec. Sys.
Fuel Sys.
Fire Sys.
Engine
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(Engine Indication and
Crew Alerting System)EICAS
Air Conditioning System Pneumatic System Fuel System
Door System Gear System Power System
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Primary Flight Display Navigation Display
Velocity
Limit, Wind Sher
Attitude
Direct. of Velocity Inc.
Auto Pilot Mode
Altitude.
Ascent/ Decent Rate
Nose Heading
Ground Speed
Wind Direct. and Speed
Nose Heading
Weather Radar
Radio Station
Aircraft Positon
Radio Station Name
Distance from Radio Station
Distance and Time to Way Point
Flight Direction
Flight Cource
Time to Planned Altitude
Way Point
Turn Direction and Point in 90 Sec.
ND of 747-400 (Map Mode)
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Air C
raft
Co
mm
un
ica
tion
HF
(2.5~22MHz)・Over Sea Long Range Communication
VHF
(117.975~
137.000MHz)
・Air Traffic Communication
・Company Communication
Satellite Communication*
・Telecommunication, Facsimile
・ADS (Automatic Dependent Surveillance)
Navig
atio
n a
nd
Gu
ida
nc
e
Radio Navigation System
・ADF(Automatic Direction Finder)
・VOR(VHF Omnidirectional Range)
・DME(Distance Measuring Equipment)
・TACAN (Tactical Air Navigation System)*
・Loran*
・Omega*
・GPS(Global Positioning System)*
Autonomous Navigation System
・Doppler Navigation System*
・INS(Inertial Navigation System)
・IRS(Inertial Reference System)
Landing Guidance System
・ILS(Instrumental Landing System)
・MLS(Microwave Landing System)
・Radio Altimeter
*not equipped in Boeing 747-400
Communication and Radio
Navigation Antenna
ATC (Air Traffic Control)
2.3 Flight Communication, Navigation and Guidance
Systems
1. Weather Radar Parabola Antenna
2. Localizer Receiver
3. Glide Slope Receiver
4. ATC Transponder Transmitter/ Receiver
5. DME Transmission/ Receiver
6. Radio Altimeter Transmitter
7. Radio Altimeter Receiver
8. Direction Finder Receiver (Loop Antenna)
9. Marker Beacon Receiver
10. VHF Transmitter/ Receiver
11. Direction Finder Transmitter
12. HF Transmitter/ Receiver
13. VOR Receiver
Advanced Course of Aerospace Guidance and Control Chapter I-2 Aircraft Systems
Direction of
Signal
Fixed Loop
Antenna
Induced Voltage
Between B-D (Loop 2)
Between H-F (Loop 1)
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ADF (Automatic Direction Finder)
Relation between Phase and Intensity of Induced Voltage
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VOR (VHF Omnidirectional Range)
VHF Carrier Wave
9.960 Hz Sub-
Carrier Wave
30 Hz Reference
Signal
9.960 Hz Signal FM
Modulated by 30Hz
Reference Phase
Signal
Phase Variable
Signal
VOR Signal
VOR Antenna
Variable 30 Hz
Reference Signal Phase Variable Signal in
terms of Direction
Synthesizer
Pre-selector Mixer Detector Filter
Variabl30Hz
Detec-tor
Filter
Control Panel
FM
Discriminator
PhaseDetec-
tor
Indicator
DriverIndicator
Navigation System or
Other Avionics
Digital DataA/D
Converter
System Block Diagram of VOR Receiver
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DME (Distance Measuring Equipment)Antenna
Duplexer
Pre-selector
IF Amplifier
Video Amplifier Decoder
Encoder
Power Amp. Modulator Synthesizer
Transmission
Tunable Voltage
Dist. Calc.
InterfaceOnboard DME
FMS etc.
Onboard DME Block Diagram
Measurement Principle of Onboard DME
Pulse Transmission
Decoder Output
Distance Gate
Distance Gate Response
Self Response
Response to Other Aircraft
Scatter Pulse
Discrimination Pulse
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INS (Inertial Navigation System)
Platform
Aircraft Aircraft
Accelerometer
Gyro
Platform
Accelerometer
Gyro Accelerometer
Gyro
Gimbal Servo
Att
itu
de
∫dt
∫dt
Gravity Acc.
and
Coriolis
Corrections
Processor
Ve
loc
ity
Po
sit
ion
Aircraft Basement
Strap-down Sensor Block
Processor
Coord.Trans.
Calculation of Trans.
Matrix
∫dt
∫dt
Gravity Acc.
and
Coriolis
Corrections
Attitude
Ve
loc
ity
Po
sit
ion
Platform System Strap-down System
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Platform System Strap-down System
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ILS (Instrumental Landing System)
LOC : Localizer
GS : Glide Slope
V 150 Hz : Amplitude of 150 Hz Modulation
V 90 Hz : Amplitude of 90 Hz Modulation
ILS Indicator
Motion of Onboard ILS Indicator
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MLS(Microwave Landing System)(1) Scanning Beam from
Direction and High-Low Guidance Unit
(2) Time Profile of Scanning Beam Angle
(3) Signal Received
(Directional Guidance Signal)
Aircraft ①
Aircraft ②
Aircraft ③
Aircraft ①
Aircraft ②
Aircraft ③
“FRO” Scan
“FRO” Scan“TO” Scan
“FRO” Scan
“TO” Scan
Be
am
S
can
nin
g
An
gle
Time
MLS Angle Measurement
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RA(Radio Altimeter)
Indicator
Altitude Signal
Video SignalTransmission Trigger Signal
ReceptorDistance
Calc.Trans-mitter
Transmission Antenna
Receiver Antenna
Transmission Pulse
Received Video Signal
Altitude Time
Fre
q.
Dif
fere
nc
eF
req
uen
cy
Modulation Cycle
Diff. Freq.
Trans. Freq.
Received Freq. Radio To-Fro
Time
Ground
Alt
itu
de
Time
Time
IndicatorDiff. Freq. Processor
Receiver Sig. Amp.
Receiver Antenna
Trans. Sig. Amp.
FM Modulation Generator
Block Diagram of FM-Type Radio Altimeter
System Diagram of
Radio AltimeterRelation between Transmission,
Receiver and Diffencial Frequency