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...
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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 |
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Engineering::Aeronautical engineering::Aircraft Engineering::Mechanical engineering::Mechanics and dynamics Zhang, Huaiyu Experimental investigation of system identification techniques for UAVs |
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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 |
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1759855288905629696 |