UWE Bristol Engineering showcase 2015

Chiu Wo Cheung
MEng Aerospace Engineering (System)
Project Supervisor
Professor Quan Min Zhu
Modelling and Control of Airbus A320
Project Summary
The aim of this project is to model an Airbus A320 by using a computer; before this can be done research of the aircraft manufacture data needs to be done
first. Therefore using data collected from the internet and book; the data results can be applied to values from equation and formulae to calculate the flight
results for the aircraft. From these, the calculated data is then computed in to software known as MATLAB and Microsoft Excel in order to develop a program
which can fit with the proposed dynamic models. Moreover, operating the MATLAB and Microsoft Excel data can demonstrate the developed prototype and
algorithm for the Airbus A320. Furthermore, the relevant data can be collected from operating MATLAB; the data will then run the program to show how the
system works, after the program has computed this information, a graph diagram will show the motion of the aircraft.
Longitudinal Stability Derivatives consider the following derivatives:
Aerodynamic Derivatives (CC XX0 and CC ZZ0 ), Speed Derivatives (CC XXuu , CC ZZuu and CC mmmm ), Angle of Attack Derivative (CC XXαα , CC ZZαα and CC mmαα ),
Rate of Angle of attack Derivatives (CC ZZαα̇ and CC mmαα̇ ) and Pitch Rate Derivatives (CC ZZqq and CC mmqq )
Longitudinal Motion consider the Phugoid Motion and Short period Oscillation:
Project Objectives
The aim of the investigation will be achieved through
the following six keys objectives
• Review up-to-data art of Airbus-A320
• Develop basic flight dynamics modelling techniques
• Develop MATLAB programs to fit the proposed
dynamic models with the measured data
• Learn to operate the MATLAB to demonstrate the
developed prototype and algorithm
• Collect relevant data from operating MATLAB
• Prepare a user-friendly demo/program manual
Variable X Z M
u
w
Variable Y L N
v
r
p
XX uu = QQQQ
mmuu 0
2CC XX0 + CC XXXX ZZ uu = QQQQ
mmuu 0
2CC ZZ0 + CC ZZZZ MM uu = QQQQcc̅
II yy uu 0
XX ww = QQQQ
mmuu 0
CC XXXX ZZ ww = QQQQ
mmuu 0
CC ZZZZ MM ww = QQQQcc̅
II yy uu 0
wẇ XX wẇ = 0 ZZ wẇ = − QQQQcc̅
2mmuu 0
2 CC ZZαα̇ MM wẇ = QQQQcc̅2
2II yy uu 0
2 CC mmαα̇
q XX qq = 0 ZZ qq = − QQQQcc̅
2mmuu 0
CC ZZZZ MM qq = QQQQcc̅2
2II yy uu 0
YY vv = QQQQ
mmuu 0
CC yyyy LL vv = QQQQQQ
II yy uu 0
CC llll NN vv = QQQQQQ
II zz uu 0
YY rr = QQQQQQ
2mmuu 0
CC yyyy LL rr = QQQQbb2
2II xx uu 0
CC llll NN rr = QQQQbb2
2II zz uu 0
YY pp = QQQQQQ
2mmuu 0
CC yyyy LL pp = QQQQbb2
2II xx uu 0
CC llll NN pp = QQQQbb2
2II zz uu 0
CC mmmm
CC mmmm
CC mmmm
CC nnnn
CC nnnn
CC nnnn
Lateral Stability Derivatives consider the following derivatives:
Angle of sideslip Derivatives (CC yyyy , CC llββ aaaaaa CC nnββ )
Yaw Rate Derivatives (CC yyrr , CC llll aaaaaa CC nnrr )
Roll Rate Derivatives (CC yyyy , CC llpp and CC nnpp )
Lateral Motion consider the Dutch Roll, Spiral Mode and Roll mode:
Project Conclusion
This report has demonstrated how to model an
Airbus A320 by using the equation and formula in
order to calculate the two different stability
derivatives, which are longitudinal stability
derivatives and lateral stability derivatives. After all
the stability derivatives have been calculated, type in
all the details about the Airbus A320 into the MATLAB
software, therefore the longitudinal Motions
(Phugoid mode and Short period oscillatory) and the
lateral Motion (Dutch roll, spiral mode and roll mode)
will be determined. Also the result has shown that
the longitudinal motion is considered in the x
direction which is the aircraft forward direction and
the z direction which is the climb and descent
direction. Moreover, lateral motion is considered in
the y direction which is about the aircraft turning left,
right and the x direction which is the aircraft’s
forward direction. In addition, this report gives an
overall idea of the aircraft analysis and shows how
results can be produced from MATLAB. Therefore, a
reasonably accurate evaluation for the Airbus A320
and a user-friendly manual can be provided for the
potential user.