飛行力学 Chapter I-3 Flight Control Systems

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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

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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

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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