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 a high speed decoy UAV
Download
index.pdf
Date
2016
Author
Baykara, Umut
Metadata
Show full item record
Item Usage Stats
622
views
255
downloads
Cite This
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 aircraft has a 6g sustained and 9g instantaneous load factor. Required payload capacity is set to be as 22 lbs,consisting of a smoke dispenser, a passive radar cross section augmenter (luneberg lens), a chaff and IR dispenser and a miss distance indicator. Since, the aim of this study is to design an optimized high speed decoy that surpasses its predecesors, a new generation CFD tool is used to achieve the high speed decoy configuration which gives the best aerodynamic performance. Baseline design and other configurations were created according to their vertical wing and tail geometry designs. All models were created in CAD environment and analyzed for different flow regimes and envelopes. Finally, configuration is selected considering various design and performance criteria.
Subject Keywords
Autonomous vehicles.
,
Flying-machines.
,
Drone aircraft.
URI
http://etd.lib.metu.edu.tr/upload/12620011/index.pdf
https://hdl.handle.net/11511/25667
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
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...
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...
Design of a medium range tactical UAV and improvement of its performance by using winglets
Turanoğuz, Eren; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2014)
The study encompasses the design, performance analysis and aerodynamic improvement of the designed medium range tactical unmanned aerial vehicle. Main requirements are set as following; cruising altitute above 3500m, endurance of approximately 10-12 hours, range of 150 km and payload of 60 kg. The conventional design phase is based on the employment of historical equations and experiences. Nowadays, employement of well known equations and experiences during the desing process are not enough to reveal a comp...
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...
Optimization of compliant parts of a hybrid trailing edge control surface of a morphing unmanned aerial vehicle
Arslan, Pınar; Gürses, Ercan; Department of Aerospace Engineering (2017)
In this thesis, optimization studies are conducted for compliant parts of a hybrid trailing edge control surface of an unmanned aerial vehicle (UAV). The geometry of the control surface was taken from a previous study conducted in [1], and then regenerated parametrically through Design Modeler tool of ANSYS Workbench v15.0. The finite element model of the control surface is created by using ANSYS Workbench v15.0 Static Structural module. The optimization study of the compliant part is conducted by using Ada...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
U. Baykara, “Design of a high speed decoy UAV,” M.S. - Master of Science, Middle East Technical University, 2016.
