Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
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
Structured H-Infinity controller design and analysis for highly maneuverable jet aircraft
Download
thesis.pdf
Date
2022-2-10
Author
Özkan, Salih Volkan
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
102
views
40
downloads
Cite This
Robust control technique is utilized to develop flight control laws for highly maneuverable aircraft. A structured H-Infinity controller is used to optimize the gains of the proposed control algorithm. For this purpose systune algorithm available in Matlab is employed to successfully obtain the controller gains satisfying selected design requirements. Designed control laws are evaluated according to these requirements and validation of the methodology is presented.
Subject Keywords
Robust Control
,
H-2/H-Infinity Methods
,
Optimal Control
,
Fly-by-wire
URI
https://hdl.handle.net/11511/96805
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Control System Design of a Vertical Take-off and Landing Fixed-Wing UAV
Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (2016-05-20)
In this study, design and implementation of control system of a vertical take-off and landing (VTOL) unmanned aerial vechicle (UAV) with level flight capability is considered. The platform structure includes both multirotor and fixed-wing (FW) conventional aircraft control surfaces: therefore named as VTOL-FW. The proposed method includes implementation of multirotor and airplane controllers and design of an algorithm to switch between them in achieving transitions between VTOL and FW flight modes. Thus, VT...
High angle attack maneuvering and stabilization control of aircraft
Ateşoğlu, Özgür; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2007)
In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologi...
Design of an autonomous landing control algorithm for a fixed wing UAV
Kargın, Volkan; Yavrucuk, İlkay; Department of Aerospace Engineering (2007)
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. ...
Experimental Investigation of Optimal Gap Distance between Rotors of a Quadrotor UAV
Kaya, Dilber Derya; Kutay, Ali Türker; Tekinalp, Ozan (2017-06-09)
The effect of spacing between the rotors of a quadrotor Unmanned Aerial Vehicle (UAV) in hovering flight is investigated. Experiments are conducted to obtain a mathematical relation between the diameter of the rotor and gap distance between each rotor. Constraints such as the maximum thrust force and minimum energy consumption are imposed. Several rotors having different sizes are tested at various RPMs with a changing gap distances, and total thrust produced by four rotors is measured. The results are give...
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 ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
S. V. Özkan, “Structured H-Infinity controller design and analysis for highly maneuverable jet aircraft,” M.S. - Master of Science, Middle East Technical University, 2022.