System identification of aerodynamic derivatives for VTOL UAV

The establishment of an Aircraft Dynamic Model is a prerequisite to design navigation and control systems. However, aerodynamic models are not easily obtained for small- scaled aircraft model such as Unmanned Aerial Vehicles (UAVs) Simulated models are important towards the development of effective...

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Main Author: Matiin Muhammad Hanifah Marican
Other Authors: Basman Elhadidi
Format: Final Year Project
Language:English
Published: Nanyang Technological University 2021
Subjects:
Online Access:https://hdl.handle.net/10356/150919
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Institution: Nanyang Technological University
Language: English
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spelling sg-ntu-dr.10356-1509192021-06-04T08:12:59Z System identification of aerodynamic derivatives for VTOL UAV Matiin Muhammad Hanifah Marican Basman Elhadidi Chan Wai Lee School of Mechanical and Aerospace Engineering mbasman@ntu.edu.sg, chan.wl@ntu.edu.sg Engineering::Aeronautical engineering The establishment of an Aircraft Dynamic Model is a prerequisite to design navigation and control systems. However, aerodynamic models are not easily obtained for small- scaled aircraft model such as Unmanned Aerial Vehicles (UAVs) Simulated models are important towards the development of effective and predictive control, given that they rely on all the aerodynamic parameters to provide information on flight characteristics. There many ways to obtain the system identification of aerodynamic derivatives. Traditionally, aircraft and rotorcraft dynamic system models have been analytically determined using Newton’s Second Law for rigid-body dynamics [1]. Longitudinal aerodynamic derivatives for a simplified UAV model was measured experimentally. The model was constrained to pitch freely while mounted on a rig placed within a wind tunnel test section. A servo motor was used to provide controlled inputs to the elevator, and an Inertial Measurement Unit (IMU) was used to measure the pitch angle and pitch rate. Experiment data were collected for various elevator deflection angles, with a varied 3211 input time pulse, at a wind tunnel speed of 7.3 m/s. The data was processed using Least Squares Method and System Identification Toolkit to obtain the transfer function of the model from which aerodynamic derivatives ! and " were calculated and analysed. Results obtained from the experiment through System Identification Toolkit were similar to theoretically calculated aerodynamic derivatives. Further research can be done to expand on multiple degrees of freedom test while taking into account limitations and recommendations discussed in this report. Bachelor of Engineering (Aerospace Engineering) 2021-06-04T08:12:58Z 2021-06-04T08:12:58Z 2021 Final Year Project (FYP) Matiin Muhammad Hanifah Marican (2021). System identification of aerodynamic derivatives for VTOL UAV. Final Year Project (FYP), Nanyang Technological University, Singapore. https://hdl.handle.net/10356/150919 https://hdl.handle.net/10356/150919 en application/pdf Nanyang Technological University
institution Nanyang Technological University
building NTU Library
continent Asia
country Singapore
Singapore
content_provider NTU Library
collection DR-NTU
language English
topic Engineering::Aeronautical engineering
spellingShingle Engineering::Aeronautical engineering
Matiin Muhammad Hanifah Marican
System identification of aerodynamic derivatives for VTOL UAV
description The establishment of an Aircraft Dynamic Model is a prerequisite to design navigation and control systems. However, aerodynamic models are not easily obtained for small- scaled aircraft model such as Unmanned Aerial Vehicles (UAVs) Simulated models are important towards the development of effective and predictive control, given that they rely on all the aerodynamic parameters to provide information on flight characteristics. There many ways to obtain the system identification of aerodynamic derivatives. Traditionally, aircraft and rotorcraft dynamic system models have been analytically determined using Newton’s Second Law for rigid-body dynamics [1]. Longitudinal aerodynamic derivatives for a simplified UAV model was measured experimentally. The model was constrained to pitch freely while mounted on a rig placed within a wind tunnel test section. A servo motor was used to provide controlled inputs to the elevator, and an Inertial Measurement Unit (IMU) was used to measure the pitch angle and pitch rate. Experiment data were collected for various elevator deflection angles, with a varied 3211 input time pulse, at a wind tunnel speed of 7.3 m/s. The data was processed using Least Squares Method and System Identification Toolkit to obtain the transfer function of the model from which aerodynamic derivatives ! and " were calculated and analysed. Results obtained from the experiment through System Identification Toolkit were similar to theoretically calculated aerodynamic derivatives. Further research can be done to expand on multiple degrees of freedom test while taking into account limitations and recommendations discussed in this report.
author2 Basman Elhadidi
author_facet Basman Elhadidi
Matiin Muhammad Hanifah Marican
format Final Year Project
author Matiin Muhammad Hanifah Marican
author_sort Matiin Muhammad Hanifah Marican
title System identification of aerodynamic derivatives for VTOL UAV
title_short System identification of aerodynamic derivatives for VTOL UAV
title_full System identification of aerodynamic derivatives for VTOL UAV
title_fullStr System identification of aerodynamic derivatives for VTOL UAV
title_full_unstemmed System identification of aerodynamic derivatives for VTOL UAV
title_sort system identification of aerodynamic derivatives for vtol uav
publisher Nanyang Technological University
publishDate 2021
url https://hdl.handle.net/10356/150919
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