Summary of Aircraft Systems 3 th
Edition
All the material needed for the HvA subject Aircraft Systems Integration of
Aviation Engineering Block 6
The following chapters are included:
1
2
3
4
6.1 – 6.5
7
8
10
11.1-11.4 & 11.11-11.12
12
1 – Flight Control Systems
1.1 – Introduction
First planes: warping wings
Actuated flight control surfaces soon after
Thereafter wires and pulleys
To overcome the high loads in transonic aircraft, powered surfaces
with hydraulically powered actuators began to be used;
o Artifical feel
o Mach trim devices
High performance aircraft experience roll/yaw coupled oscillation
(Dutch roll)
o Yaw dampers
o Auto stabilization systems
Category III auto land system manufactured by Smiths Industries
and fitted to the Trident and Belfast Aircraft.
CSAS: Control and Stability Augmentation System, fitted on the
Tornado, hybrid fly-by-wire
Fly-by-wire: A320, A330, A340, B777
1.2 – Principles of Flight Control
Pitch nose up/down
Roll turn
1
, Yaw change in heading
1.3 – Flight Control Surfaces
Ailerons
Elevators
Rudder
1.4 – Primary Flight Control
Pitch, roll, yaw
1.5 – Secondary Flight Control
High lift control is provided by a combination of flaperons and
leading edge slats
Eurofighter Typhoon has airbrakes located on the upper rear
fuselage
1.6 – Commercial Aircraft
Primary flight control:
o Pitch control is exercised by four elevators located on the
trailing edge of the tail plane
Each elevator is independently powered by flight control
actuator
o Roll control is provided by two ailerons on the outboard trailing
edge of the wing
At low speeds wing spoilers, mounted on the wing, assist
the aileron
o Yaw control is provided by three independent rudders located
on the trailing edge of the fin
Associated with yaw-dampers
Secondary flight control:
o Flap control is located on the inboard of the wing trailing edges
App. 5 per wing
o Slates located in the wing leading edge
Increase wing area and camber, just like flaps
o Speed brakes; over-wing spoilers
1.7 – Flight Control Linkage Systems
Pitch control: moving the control column forward and backward
Roll control: moving the control column from side to side
Yaw control: rudder pedals; left rudder pedal will yaw aircraft to the
left
Methods of connection:
o Push-pull control by rod systems
2
Edition
All the material needed for the HvA subject Aircraft Systems Integration of
Aviation Engineering Block 6
The following chapters are included:
1
2
3
4
6.1 – 6.5
7
8
10
11.1-11.4 & 11.11-11.12
12
1 – Flight Control Systems
1.1 – Introduction
First planes: warping wings
Actuated flight control surfaces soon after
Thereafter wires and pulleys
To overcome the high loads in transonic aircraft, powered surfaces
with hydraulically powered actuators began to be used;
o Artifical feel
o Mach trim devices
High performance aircraft experience roll/yaw coupled oscillation
(Dutch roll)
o Yaw dampers
o Auto stabilization systems
Category III auto land system manufactured by Smiths Industries
and fitted to the Trident and Belfast Aircraft.
CSAS: Control and Stability Augmentation System, fitted on the
Tornado, hybrid fly-by-wire
Fly-by-wire: A320, A330, A340, B777
1.2 – Principles of Flight Control
Pitch nose up/down
Roll turn
1
, Yaw change in heading
1.3 – Flight Control Surfaces
Ailerons
Elevators
Rudder
1.4 – Primary Flight Control
Pitch, roll, yaw
1.5 – Secondary Flight Control
High lift control is provided by a combination of flaperons and
leading edge slats
Eurofighter Typhoon has airbrakes located on the upper rear
fuselage
1.6 – Commercial Aircraft
Primary flight control:
o Pitch control is exercised by four elevators located on the
trailing edge of the tail plane
Each elevator is independently powered by flight control
actuator
o Roll control is provided by two ailerons on the outboard trailing
edge of the wing
At low speeds wing spoilers, mounted on the wing, assist
the aileron
o Yaw control is provided by three independent rudders located
on the trailing edge of the fin
Associated with yaw-dampers
Secondary flight control:
o Flap control is located on the inboard of the wing trailing edges
App. 5 per wing
o Slates located in the wing leading edge
Increase wing area and camber, just like flaps
o Speed brakes; over-wing spoilers
1.7 – Flight Control Linkage Systems
Pitch control: moving the control column forward and backward
Roll control: moving the control column from side to side
Yaw control: rudder pedals; left rudder pedal will yaw aircraft to the
left
Methods of connection:
o Push-pull control by rod systems
2
