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
Vision-aided landing for fixed wing unmanned aerial vehicle
Download
index.pdf
Date
2016
Author
Esin, Engin
Metadata
Show full item record
Item Usage Stats
332
views
165
downloads
Cite This
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 designed system by sending control messages to landing autopilot, ground control station (GCS) software is developed. By using GCS interface, one can send commands to landing autopilot to analyze performance of the landing autopilot, activate or deactivate functions of the landing autopilot, change position data source as visual positioning system (VPS) or global positioning system (GPS) and change flight mode of the UAV. Besides testing and analyzing the system, GCS is used to prepare flight plans for landing. Waypoints of the prepared flight plan is applied by landing autopilot to keep trajectory points between two coordinates with keeping altitude and speed requests. To be able to manage that mission, waypoints include latitude, longitude, heading, altitude and speed specifications. Therefore, to be able to execute these waypoints; roll, pitch, altitude, heading and speed controllers are designed. On the image processing side, position of aircraft is detected with respect to a known sized runway. This differential position information, which is obtained by image processing, is used instead of GPS information by landing autopilot to make a safe landing. Developed system has been successfully tested in flight simulation environment under several different wind and turbulence conditions with different initial orientations of the UAV.
Subject Keywords
Drone aircraft.
,
Flying-machines.
,
Autonomous vehicles.
,
Vehicles, Remotely piloted.
,
Landing aids (Aeronautics).
URI
http://etd.lib.metu.edu.tr/upload/12620093/index.pdf
https://hdl.handle.net/11511/25748
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Aerodynamic and structural design and analysis of an electric powered mini UAV
Demircan, Alpay; Kayran, Altan; Department of Aerospace Engineering (2016)
The aim of this study is to describe the aerodynamic and structural design of an electric powered portable Mini UAV. Conceptual design, structural design and analysis of the wing and detail design phases of the UAV are presented in the study. Fixed wing mini UAV configuration with fixed – pitch propeller has been chosen for the design. In order to provide multi-mission capability, payload of the UAV is designed as a replaceable mission compartment. System requirements and mission profiles of the airplane ar...
Conceptual design of a stealth unmanned combat aerial vehicle with multidisciplinary design optimization
Çakın, Uğur; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2018)
The present study aims to develop a methodology for multi-disciplinary design optimization (MDO) of an unmanned combat aerial vehicle. At the current stage of optimization study, three disciplines are considered, which are aerodynamics, structural weight and radar cross section (RCS) signature. As objective functions, maximum range and minimum RCS signature are employed. To generate pareto-optimal solutions, multi-objective particle swarm optimization (MOPSO) function of MATLAB® is performed. To get aerodyn...
Landing autopilot design for an unmanned aerial vehicle /
Ak, Ayşe İlden; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2014)
In this thesis, studies for the development of a landing autopilot for the UAV (Unmanned Aerial Vehicle), Pioneer RQ2 are presented. Firstly, 6 DOF (degree of freedom) nonlinear model of Pioneer is implemented in Matlab-Simulink based on FDC (Flight Dynamics and Control) Toolbox. Then, in accordance with steady-state wings level flight condition, trim points are found for different airspeed values, constant height and zero flight path angle. The nonlinear model of Pioneer is linearized at these trim points ...
Design of a high speed decoy UAV
Baykara, Umut; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2016)
This study consists of design, CFD aerodynamic analysis and optimized selection of a high speed decoy UAV. The mission requirements for the high speed decoy are based upon the previous experiences in literature. The requirements are specified as: Maximum altitude of 15000 ft, maximum speed of 450 kts and an endurance of at least 1 hour. The decoy UAV is launched from a pneumatic catapult and lands via a parachute system. It is a highly agile aircraft having a very high maneuverability capability. The aircra...
Navigation algorithms and autopilot application for an unmanned airvehicle
Kahraman, Eren; Alemdaroğlu, Hüseyin Nafiz; Nalbantoğlu, Volkan; Department of Aerospace Engineering (2010)
This study describes the design and implementation of the altitude and heading autopilot algorithms for a fixed wing unmanned air vehicle and navigation algorithm for attitude and heading reference outputs. Algorithm development is based on the nonlinear mathematical model of Middle East Technical University Tactical Unmanned Air Vehicle (METU TUAV), which is linearized at a selected trim condition. A comparison of nonlinear and linear mathematical models is also done. Based on the linear mathematical model...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
E. Esin, “Vision-aided landing for fixed wing unmanned aerial vehicle,” M.S. - Master of Science, Middle East Technical University, 2016.