Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Design of an autonomous landing control algorithm for a fixed wing UAV
Download
index.pdf
Date
2007
Author
Kargın, Volkan
Metadata
Show full item record
Item Usage Stats
1123
views
545
downloads
Cite This
This thesis concerns with the design and development of automatic flight controller strategies for the autonomous landing of fixed wing unmanned aircraft subject to severe environmental conditions. The Tactical Unmanned Aerial Vehicle (TUAV) designed at the Middle East Technical University (METU) is used as the subject platform. In the first part of this thesis, a dynamic model of the TUAV is developed in FORTRAN environment. The dynamic model is used to establish the stability characteristics of the TUAV. The simulation model also incorporates ground reaction and atmospheric models. Based on this model, the landing trajectory that provides shortest landing distance and smallest approach time is determined. Then, an automatic flight control system is designed for the autonomous landing of the TUAV. The controller uses a model inversion approach based on the dynamic model characteristics. Feed forward and mixing terms are added to increase performance of the autopilot. Landing strategies are developed under adverse atmospheric conditions and performance of three different classical controllers are compared. Finally, simulation results are presented to demonstrate the effectiveness of the design. Simulation cases include landing under crosswind, head wind, tail wind, wind shear and turbulence.
Subject Keywords
Motor Vehicles.
,
Astronautics.
URI
http://etd.lib.metu.edu.tr/upload/12608996/index.pdf
https://hdl.handle.net/11511/16994
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Vision-aided landing for fixed wing unmanned aerial vehicle
Esin, Engin; Kutay, Ali Türker; Department of Aerospace Engineering (2016)
The aim of this thesis is to design an autoland system for fixed wing unmanned aerial vehicle (UAV) to make auto landing by using position information calculated by image processing algorithms. With this ability, even if GPS is not available to be used, UAV still could make a safe automatic landing. Landing autopilot is aimed to keep UAV on a straight line with a constant flight path angle. Therefore, landing autopilot and computer vision methods are studied within the scope of this thesis. Also, to test de...
Design and analysis of a mode-switching micro unmanned aerial vehicle
Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (SAGE Publications, 2016-12-01)
In this study, design and analysis of a mode-switching vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) with level flight capability is considered. The design of the platform includes both multirotor and fixed-wing (FW) conventional airplane structures; therefore named as VTOL-FW. The aircraft is modeled using aerodynamical principles including post-stall conditions. Trim conditions are obtained by solving constrained optimization problems. Linear analysis techniques are utilized for trim ...
Aerodynamic design and control of tandem wing unmanned aerial vehicle
Kaya, Taşkın; Özgen, Serkan; Department of Aerospace Engineering (2019)
This thesis presents an approach towards the design methodology of electrical propulsion, tandem wing unmanned aerial vehicle. Due to its possible rewarding features, tandem wing design is investigated as the main subject of this study. The stability and control characteristics of tandem wing aircraft are critical since the interference between the two wings may result in nonlinear aerodynamic characteristics for varying angles of attack. Thus, the design of the controller system requires careful handling, ...
Havacılık Nöroergonomisinde Optik Beyin Görüntüleme Uygulamaları
Çakır, Murat Perit (2021-06-01)
Pilotların, insansız hava aracı operatörlerinin, hava trafik kontrolörlerinin eğitim ve uçuş faaliyetleri sırasında bilişsel durumlarının takibini sağlayacak nesnel yöntemlerin geliştirilmesi uçuş emniyetinin sağlanması, eğitim süreçlerinin optimizasyonu ve yenilikçi insan-makine arayüzlerinin tasarımı bakımından kritik önem taşımaktadır. İşlevsel Yakın-Kızılötesi Tayfölçümü (functional near infrared spectroscopy – fNIRS) optik beyin görüntüleme teknolojisi gibi saha kullanımına uygun, portatif ve güvenilir...
Design and aerodynamic analysis of a VTOL tilt-wing UAV
Cakir, Hasan; Kurtuluş, Dilek Funda (2022-01-01)
The aerodynamic design and analysis of an Unmanned Air Vehicle, capable of vertical take-off and landing by employing fixed four rotors on the tilt-wing and two rotors on the tilt-tail, will be presented in this study. Both main wing and the horizontal tail can be tilted 90 degrees. During VTOL, transition and forward flight, aerodynamic and thrust forces have been employed. Different flight conditions, including the effects of angle of attack, side slip, wing tilt angle and control surfaces deflection angl...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
V. Kargın, “Design of an autonomous landing control algorithm for a fixed wing UAV,” M.S. - Master of Science, Middle East Technical University, 2007.
