Experimental investigation of system identification techniques for UAVs

UAVs are known for their remarkable performance and flexibility compared to their manned counterparts. As most UAVs are highly automated and rely predominantly on their flight control systems to maintain stability during flight, it is paramount to identify their aerodynamic derivatives, which...

Full description

Saved in:
Bibliographic Details
Main Author: Zhang, Huaiyu
Other Authors: Basman Elhadidi
Format: Final Year Project
Language:English
Published: Nanyang Technological University 2022
Subjects:
Online Access:https://hdl.handle.net/10356/157655
Tags: Add Tag
No Tags, Be the first to tag this record!
Institution: Nanyang Technological University
Language: English
id sg-ntu-dr.10356-157655
record_format dspace
spelling sg-ntu-dr.10356-1576552023-03-04T20:06:43Z Experimental investigation of system identification techniques for UAVs Zhang, Huaiyu Basman Elhadidi Chan Wai Lee School of Mechanical and Aerospace Engineering chan.wl@ntu.edu.sg, mbasman@ntu.edu.sg Engineering::Aeronautical engineering::Aircraft Engineering::Mechanical engineering::Mechanics and dynamics UAVs are known for their remarkable performance and flexibility compared to their manned counterparts. As most UAVs are highly automated and rely predominantly on their flight control systems to maintain stability during flight, it is paramount to identify their aerodynamic derivatives, which are associated with stability and control responses of the aircraft. Doing so will facilitate structural design of the UAVs, as well as the development of their flight control systems. This final year project report proposes an innovative experimental methodology for the evaluation of aerodynamic derivatives of UAV models. The project takes both theoretical and experimental approaches to obtain the model’s pitching moment and normal force derivatives. The theoretical approach looked into flight dynamics and control theory, from which theoretical value of aerodynamic derivatives could be calculated. On the other hand, the experimental approach involved design and fabrication of a UAV test model, which was integrated with IMU and load cell. The experiment was conducted in two phases in the form of wind tunnel testing, with the first phase designed as free pitching motion of the model with its pitch rate recorded. This allowed the evaluation of pitching moment derivatives through parameter identification with the aid of MATLAB Curve Fitting Toolbox. Natural frequency and damping ratio could also be obtained through this process. The second phase of the experiment measured the normal force experienced by the model with a load cell, so that normal force derivatives could be determined by performing system identification with MATLAB SI Toolbox. The experiment results were compared against theoretical values to evaluate the accuracy of the experimental methodology proposed. The values obtained through parameter and system identification were of close resemblance to theoretical calculations, with minor differences in the transfer function model of normal force derivatives. The scope of future works could potentially be extended to study UAV models with more complicated structures and multiple degrees of freedom. Bachelor of Engineering (Aerospace Engineering) 2022-05-21T13:23:53Z 2022-05-21T13:23:53Z 2022 Final Year Project (FYP) Zhang, H. (2022). Experimental investigation of system identification techniques for UAVs. Final Year Project (FYP), Nanyang Technological University, Singapore. https://hdl.handle.net/10356/157655 https://hdl.handle.net/10356/157655 en B343 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::Aircraft
Engineering::Mechanical engineering::Mechanics and dynamics
spellingShingle Engineering::Aeronautical engineering::Aircraft
Engineering::Mechanical engineering::Mechanics and dynamics
Zhang, Huaiyu
Experimental investigation of system identification techniques for UAVs
description UAVs are known for their remarkable performance and flexibility compared to their manned counterparts. As most UAVs are highly automated and rely predominantly on their flight control systems to maintain stability during flight, it is paramount to identify their aerodynamic derivatives, which are associated with stability and control responses of the aircraft. Doing so will facilitate structural design of the UAVs, as well as the development of their flight control systems. This final year project report proposes an innovative experimental methodology for the evaluation of aerodynamic derivatives of UAV models. The project takes both theoretical and experimental approaches to obtain the model’s pitching moment and normal force derivatives. The theoretical approach looked into flight dynamics and control theory, from which theoretical value of aerodynamic derivatives could be calculated. On the other hand, the experimental approach involved design and fabrication of a UAV test model, which was integrated with IMU and load cell. The experiment was conducted in two phases in the form of wind tunnel testing, with the first phase designed as free pitching motion of the model with its pitch rate recorded. This allowed the evaluation of pitching moment derivatives through parameter identification with the aid of MATLAB Curve Fitting Toolbox. Natural frequency and damping ratio could also be obtained through this process. The second phase of the experiment measured the normal force experienced by the model with a load cell, so that normal force derivatives could be determined by performing system identification with MATLAB SI Toolbox. The experiment results were compared against theoretical values to evaluate the accuracy of the experimental methodology proposed. The values obtained through parameter and system identification were of close resemblance to theoretical calculations, with minor differences in the transfer function model of normal force derivatives. The scope of future works could potentially be extended to study UAV models with more complicated structures and multiple degrees of freedom.
author2 Basman Elhadidi
author_facet Basman Elhadidi
Zhang, Huaiyu
format Final Year Project
author Zhang, Huaiyu
author_sort Zhang, Huaiyu
title Experimental investigation of system identification techniques for UAVs
title_short Experimental investigation of system identification techniques for UAVs
title_full Experimental investigation of system identification techniques for UAVs
title_fullStr Experimental investigation of system identification techniques for UAVs
title_full_unstemmed Experimental investigation of system identification techniques for UAVs
title_sort experimental investigation of system identification techniques for uavs
publisher Nanyang Technological University
publishDate 2022
url https://hdl.handle.net/10356/157655
_version_ 1759855288905629696