chapter 3 flight control systems...computer series servo rol k power actuator aero. control surface...
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飛行力学 Chapter I-3 Flight Control Systems
1
Chapter 3 Flight Control Systems
Evolution of Flight Control Systems
3.1 Evolution of Flight Control Systems
Simple Cable (or Pushrod)
Hydraulic Boost
Fully Powered Controls
Stability Augmentation System (SAS)
Control Augmentation System (CAS)
Fly by Wire
飛行力学 Chapter I-3 Flight Control Systems
2
Aerodynamic Control
Surface System
Control System
Rudder
ElevatorRight Aileron
Control Stick
Foot Pedal Left Aileron
Wing Warp (Twist) System
Flyer by Light Brothers
飛行力学 Chapter I-3 Flight Control Systems
3
Tab: Small sub-surface to assist the control surface
deflection
Trim Tab
Balance Tab
Servo Tab
Spring Tab
Control StickControl Stick
Control Stick Control Stick
Trim Wheel
Universal Joint Trailing Edge Down
0t
Aerodynamic Control Surface
Tab
飛行力学 Chapter I-3 Flight Control Systems
4
Conventional Mechanical
Control System
Fly-by-Wire Control System
Advantage of Fly by Wire
Simple System
Reduction in Weight
Volume Efficient
Higher Reliability
Good Maintainability
Integration of Control
Augmentation
Independent of Structure
Deformation
Improved Cockpit Layout
Flexible in Aerodynamic
Shape
Reduction of Development
and Aircraft Cost
Lateral Control
Control Command Sensor (Transducer)
Control Stick
Electric Wire
Motion SensorServo Valve
Aileron Actuator
Elevator Actuator
Electric Unit (Computer)
Servo Valve
Control Command Sensor (Transducer)
Hydraulic Line
Hydraulic Line
Pitch Control
Hyd
rau
lic
Sys
tem
En
gin
e S
ys
tem
飛行力学 Chapter I-3 Flight Control Systems
5Evolution of Aircraft Automatic Flight Control System
3.2 Automatic Flight
Control System
Gyro System
1st Generation:
Mechanical Autopilot System
1900
2nd Generation:
Electronic Autopilot System
3rd Generation:
Automatic Landing System
4th Generation:
Digital Flight Management
System (FMS)
5th Generation:
Advanced FMS
1920 1940 1960 1980 2000 2020
飛行力学 Chapter I-3 Flight Control Systems
Improvement of Flight Characteristics
6
Flight Control Technology
SAS (Stability Augmentation System)
CAS (Control Augmentation System)
FBW (Fly by Wire System)*
FMS (Flight Management System)
Reduction of
Pilot Work Loads
Flight
Control
* ACT (Active Control
Technology)
SAS
CASFBW
Motion
Sensor
SAC Computer
Co
ntr
ol
Sti
ck
Series
Servo
Power Actuator
Aero. Control Surface
Motion
Sensor
SAC Computer
Series
Servo
Co
ntr
ol
Sti
ck
Power Actuator
Aero. Control Surface
Co
ntr
ol
Sti
ck
Power Actuator
Aero. Control Surface
Motion
Sensor
FBW Computer
SecondActuator
飛行力学 Chapter I-3 Flight Control Systems
7
Active Control Technologies
(FBW :Fly-By-WIRE System)
Improvement of
Aerodynamic
Characteristics
Improvement
of Structure
Characteristics
Active Control
Technologies
Relaxed Static
Stability
Controllability
Reinforcement
Maneuver Load
Control
Direct Lift/Side
Force Control
Flight Envelope
Expansion
Mission
Adaptive Wing
Load
Alleviation
Structure
Mode
Control
Helicopter:
Vibration
Control
Maneuver
Load
Control
Gust Load
Control
Ride
Control
Work
Load
Reduction
Flutter
Mode
Control
飛行力学 Chapter I-3 Flight Control Systems
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F117(Nighthawk)
Length :38ft(11.6m)Span :22ft(約6.7m)Wing Sweep Angle :72.5deg
Max. Takeoff Weight :12,000lb (5,433kg)
Passenger :1
B2(Spirit)
Length :21.03m
Span :52.43m
Height :5.18m
Max. Speed :1,000km/h
Cruise Speed :M0.8
Empty Weight :45t
Max. Takeoff Weight :170t
Payload :18t
Engine:GE F118-GE-100
Turbo-Fan Engine×4基Thrust :77.0kN
Flight Lange :12,000km
Passenger :2名
Relaxed Static
StabilityControllability
Reinforcement
飛行力学 Chapter I-3 Flight Control Systems
9Relaxed Static Stability (RSS) Maneuver Load Control (MLC)
Conventional Aircraft
RSS Aircraft
Conventional Aircraft
RSS Aircraft
Sub-sonic Speed
Super-sonic Speed
RSS
Conventional Aircraft
CG
Lim
it
Subsonic Supersonic
Conventional Aircraft
Conventional Aircraft
Maneuver Load Control
Maneuver Load Control
Conventional Load
Conventional Load
Maneuver Load
Control Surface
Wing Load
Shear
Bending Moment
Root
Root
Wing Tip
Wing Tip
Active Flight control of Lockheed L-1011
飛行力学 Chapter I-3 Flight Control Systems
10Direct Force Control
Ballast
Flapperon
Aileron
with FMC
without FMC
Dam
pin
g
Flight Velocity (m/s)
Flutter Mode Control
Rudder
Horizontal Canard
Wing TE Flap
Vertical Canard
T2-CCV Test Aircraft