AeE 402 AIRCRAFT SYSTEM DYNAMICS
AND VIBRATION
LECTURE NO. 1
Aircraft Systems
(Summary)
BY: DR. JAY JACK R. MANZANO
Topic for Discussion:
Aircraft Systems:
1.
2.
3.
4.
5.
Flight Control Systems
Engine Control Systems
Fuel Systems
Hydraulic Systems
Electrical Systems
Note: All sourced-out pictures and diagrams are for educational purposes only
FLIGHT CONTROL SYSTEMS
Principles of Flight Controls:
The motion of an aircraft is defined in relation to translational motion and
rotational motion around a fixed set of axes. Translational motion is that by
which a vehicle travels from one point to another in space. For an orthodox
aircraft the direction in which translational motion occurs is in the direction
in which the aircraft is flying, which is also the direction in which the aircraft
is flying, which is also the direction in which it is pointing. The rotational
motion related to the motion of the aircraft around three defined axes; pitch,
roll , and yaw
Primary Flight Control (Commercial):
Primary flight control systems consists of ailerons, elevator, and rudder and
required to control the aircraft safely during flight. This are attached to the
airframe on hinges or tracks so that they may move and thus deflect the air
stream passing over them. This redirection of the air stream generates an
unbalanced force to rotate the plane about the associated axis
Secondary Flight Control (Commercial):
Secondary flight controls are intended to improve the aircraft performance
characteristics or to relieve excessive control loading, and consist of high
lift devices such as slats, and flaps as well as flight spoilers and trim
systems.
ENGINE CONTROL SYSTEMS
Aircraft engine controls provide a means for the pilot to control and monitor
the operation of the aircraft’s powerplant.
In an aircraft with a fixed-pitch propeller, there is no direct control over the
propeller rotational speed which depends on the airspeed and loading. The
pilot has to pay attention to the RPM indicator and adjust the throttle/power
lever in order to maintain the desired constant speed of the propeller. When
the airspeed reduces and the loading increases (ie. In climb), RPM will
decrease and the pilot has to increase the throttle/power. When the airspeed
increases and the loading decreases (ie. In a dive), the RPM will increase and
the pilot has to decrease the throttle/power in order to prevent RPM from
exceeding the operational limits and damaging the motor.
For a Jet aircraft, it employs FADEC consisting of a digital computer, called an
Electronic Engine Controller (EEC) or Engine Control Unit (ECU), and its
related accessories that control all aspects of aircraft engine performance.
FADEC is an acronym for Full Authority Digital Engine Control, a computermanaged aircraft ignition and engine control system used in modern
commercial and military aircraft to control all aspects in place of analog
electronic controls
Opposed Piston Aircraft Engine
Aircraft Radial Engine
Aircraft Jet Engine
Turbo Fan Aircraft Engine
FADEC for Piston Engines
FADEC – Full Authority Digital Engine Control
FADEC for Jet Engine
Typical Picture Diagram of FADEC
FUEL SYSTEMS
The essential characteristics of a modern aircraft fuel management system
may embrace some or all of the following modes of operation
• Fuel pressurization
• Engine feed
• Fuel transfer
• Refuel/defuel
• Fuel storage- there are many issues related to the storage and assured
supply of fuel during aircraft flight; these issues vary from aircraft to
aircraft and form the kernel of the overall aircraft fuel system
requirements
• Vent systems
• Use of fuel as heat sink
• Fuel jettison
• In-flight re-fueling
Typical Piston Engine Fuel
Diagram
Filter and Drain to check contaminants in the fuel (gascolator)
Fuel Vent System for Piston Type Aircraft
Fuel Vent (Remove Before Flight)
A-380 Detailed Fuel Systems
Aerial Refueling Systems
HYDRAULIC SYSTEMS
Majority of aircraft is use today need hydraulic power for a number of tasks.
Many of the functions to be performed affect the safe operation of the aircraft
and must not operate incorrectly, i.e. must operate when commanded, must
not operate when not commanded and must not fail totally under single
failure conditions.
Primary Flight Controls:
• Elevators
• Rudders
• Ailerons
• Canards
Secondary Flight Controls:
• Flaps
• Slats
• Spoilers
• Airbrakes
Utility Systems:
• Undercarriage –gear and doors
• Wheel-brakes and anti-skid
• Parking brake
• Nosewheel steering
• In-flight refueling probe
• Cargo doors
• Loading ramp
• Passenger stairs
• Bomb bay doors
• Gun purging scoop
• Canopy actuation
Hydraulic Systems for Small Aircraft
Vibration Analysis and Control Technologies for Commercial Aircraft
Pipeline Damaged due to
Vibration
ELECTRICAL SYSTEMS
Ground Power Unit (GPU) for Commercial Aircraft
Auxiliary Power Unit (APU) for Commercial Aircraft
End of Lecture No. 1