Mathematical Modelling of an Unmanned Aerial Vehicle
This thesis presents the results of a study on the development of a mathematical model of the flight dynamics of a smallscaled aircraft. The aircraft, due to its small size has the potential to be converted to an unmanned aerial vehicle (UAV). A mathematical model of an aircraft flight dynamics...
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2005

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myupmir.612920231011T02:54:39Z Mathematical Modelling of an Unmanned Aerial Vehicle 200511 Chong, Chiew Choy This thesis presents the results of a study on the development of a mathematical model of the flight dynamics of a smallscaled aircraft. The aircraft, due to its small size has the potential to be converted to an unmanned aerial vehicle (UAV). A mathematical model of an aircraft flight dynamics can be derived through wind tunnel testing or Computational Fluid Dynamics (CFD) analysis. But the work presented in this study develops an alternative method by means of flight testing. The method shows that by proper analysis of the data from sensors that measure the aircraft state variables such as pitch angle, altitude, speed, a profile of the aircraft flight dynamics can be deduced. it is expected that the results h mth is study will benefit projects which interest is to convert existing flyable aircraft to be an UAV, such as the Composites Technology Research Malaysia (CTRM) project in Eagle Airborne Reconnaissance Vehicle (ARV) System. In this study, a smallscaled remotecontrolled plane was equipped with onboard sensors and a data logger. A software program has been written for this project which intedaced the datalogging system, with a computer aided engineering (CAE) software MATLAB and its toolbox SIMULINK. Using the program developed, a profile of the aircraft longitudinal motion was collected through a series of flight tests. It was found that the aircraft longitudinal dynamics developed can be represented as a simple second order transfer function equation. Using the correlation coefficient method, it was found that 99.5% of the variability in short period flight test result is explained by the simulation result while 87.5% of the variability in Phugoid flight test result is explained by the simulation result. The results and method proposed in this study helps to recreate the flight dynamic characteristics of the smallscaled aircraft through flight simulation, which will be important for such work as control law determination in the future. Drone aircraft  Mathematical models  case studies 200511 Thesis http://psasir.upm.edu.my/id/eprint/6129/ http://psasir.upm.edu.my/id/eprint/6129/1/FK_2006_49.pdf text en public masters Universiti Putra Malaysia Drone aircraft  Mathematical models  case studies Engineering Zaludi, Zairil Azhar English 
institution 
Universiti Putra Malaysia 
collection 
PSAS Institutional Repository 
language 
English English 
advisor 
Zaludi, Zairil Azhar 
topic 
Drone aircraft  Mathematical models  case studies 
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Drone aircraft  Mathematical models  case studies Chong, Chiew Choy Mathematical Modelling of an Unmanned Aerial Vehicle 
description 
This thesis presents the results of a study on the development of a mathematical
model of the flight dynamics of a smallscaled aircraft. The aircraft, due to its small
size has the potential to be converted to an unmanned aerial vehicle (UAV). A
mathematical model of an aircraft flight dynamics can be derived through wind
tunnel testing or Computational Fluid Dynamics (CFD) analysis. But the work
presented in this study develops an alternative method by means of flight testing. The
method shows that by proper analysis of the data from sensors that measure the
aircraft state variables such as pitch angle, altitude, speed, a profile of the aircraft
flight dynamics can be deduced. it is expected that the results h mth is study will
benefit projects which interest is to convert existing flyable aircraft to be an UAV,
such as the Composites Technology Research Malaysia (CTRM) project in Eagle
Airborne Reconnaissance Vehicle (ARV) System. In this study, a smallscaled
remotecontrolled plane was equipped with onboard sensors and a data logger. A
software program has been written for this project which intedaced the datalogging
system, with a computer aided engineering (CAE) software MATLAB and its
toolbox SIMULINK. Using the program developed, a profile of the aircraft
longitudinal motion was collected through a series of flight tests. It was found that the aircraft longitudinal dynamics developed can be represented as a simple second
order transfer function equation. Using the correlation coefficient method, it was
found that 99.5% of the variability in short period flight test result is explained by the
simulation result while 87.5% of the variability in Phugoid flight test result is
explained by the simulation result. The results and method proposed in this study
helps to recreate the flight dynamic characteristics of the smallscaled aircraft
through flight simulation, which will be important for such work as control law
determination in the future. 
format 
Thesis 
qualification_level 
Master's degree 
author 
Chong, Chiew Choy 
author_facet 
Chong, Chiew Choy 
author_sort 
Chong, Chiew Choy 
title 
Mathematical Modelling of an Unmanned Aerial Vehicle 
title_short 
Mathematical Modelling of an Unmanned Aerial Vehicle 
title_full 
Mathematical Modelling of an Unmanned Aerial Vehicle 
title_fullStr 
Mathematical Modelling of an Unmanned Aerial Vehicle 
title_full_unstemmed 
Mathematical Modelling of an Unmanned Aerial Vehicle 
title_sort 
mathematical modelling of an unmanned aerial vehicle 
granting_institution 
Universiti Putra Malaysia 
granting_department 
Engineering 
publishDate 
2005 
url 
http://psasir.upm.edu.my/id/eprint/6129/1/FK_2006_49.pdf 
_version_ 
1783725687146807296 