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
Aeroelastic analyses of an unmanned helicopter
Download
Alaaddin Furkan UZUNKAYA MSc Thesis.pdf
Date
2023-4-14
Author
Uzunkaya, Alaaddin Furkan
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
199
views
161
downloads
Cite This
In helicopter comprehensive analysis tools, helicopter blades could be modeled as rigid beams in torsional direction; however, it is well known that helicopter blades are very flexible structures. One of the main purposes of this thesis is to analyze the effects of torsional twist on the helicopter’s performance characteristics and to examine validity of rigid blade assumption. To perform the analyses, aerodynamic loads are calculated by using blade element momentum theory. In elastic blade analyses, aerodynamic loads cause a torsional twist which increments aerodynamic load field on the blade. On the other hand, there is no torsional twist and aerodynamic load increment in the rigid blade assumption. A trim code is written to obtain trim points for a level flight at sea level by using rigid and elastic blade in which the only difference is the torsional twist and aerodynamic increments due to the torsional twist. In the second part of the thesis, flutter analyses are conducted for the reference blade by using steady aerodynamic loads, Theodorsen’s, Loewy’s and a modified version of Loewy’s unsteady aerodynamic theories.
Subject Keywords
Aeroelasticity
,
Unmanned helicopter
,
Flutter
,
Theodorsen
,
Loewy
URI
https://hdl.handle.net/11511/103097
Collections
Graduate School of Natural and Applied Sciences, Thesis
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
A. F. Uzunkaya, “Aeroelastic analyses of an unmanned helicopter,” M.S. - Master of Science, Middle East Technical University, 2023.