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
Flight flutter testing and aeroelastic stability of aircraft
Date
2007-01-01
Author
Kayran, Altan
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
276
views
0
downloads
Cite This
Purpose - This paper sets out to provide a general review of the flight flutter test techniques utilized in aeroelastic stability flight testing of aircraft, and to highlight the key items involved in flight flutter testing of aircraft, by emphasizing all the main information processed during the flutter stability verification based on flight test data.
Subject Keywords
Aerodynamics
,
Flight dynamics
,
Aircraft
URI
https://hdl.handle.net/11511/39858
Journal
AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY
DOI
https://doi.org/10.1108/00022660710780623
Collections
Department of Aerospace Engineering, Article
Suggestions
OpenMETU
Core
Flight flutter testing and aeroelastic stability of aircraft
Kayran, Altan (2007-01-01)
Purpose - To provide a general review of the flight flutter test techniques utilized in aeroelastic stability flight testing of aircraft, and to highlight the key items involved in flight flutter testing of aircraft, by emphasizing all the main information processed during the flutter stability verification based on flight test data.
Aerodynamic parameter estimation using flight test data
Kutluay, Ümit; Platin, Bülent Emre; Mahmutyazıcıoğlu, Gökmen; Department of Mechanical Engineering (2011)
This doctoral study aims to develop a methodology for use in determining aerodynamic models and parameters from actual flight test data for different types of autonomous flight vehicles. The stepwise regression method and equation error method are utilized for the aerodynamic model identification and parameter estimation. A closed loop aerodynamic parameter estimation approach is also applied in this study which can be used to fine tune the model parameters. Genetic algorithm is used as the optimization ker...
Flutter qualification of transport aircraft with store suspension
Kayran, Altan (2004-01-01)
The methodology backed by relevant analysis results, flutter flight test (FFT) results, and their interpretation is presented for the flutter qualification of a transport aircraft with wing mounted external store suspension. Before the flight tests, extensive flutter analyses are performed by MSC/Nastran for different weight and CG configurations to reduce the number of costly FFTs based on the results of flutter analysis and decide on the aircraft test configurations. Analysis results and test results indi...
Aircraft motion dynamics and lateral trajectory tracking algorithm design for the enhancement of flight safety
Günhan, Cahide Yeliz; Demirbaş, Kerim; Department of Electrical and Electronics Engineering (2018)
This thesis aspires to cover the fundamentals of an aircraft control for Flight Management System (FMS). FMS, trajectory tracking and performance requirements of a flight are the focal points of the thesis. In view of this, the thesis consists of the outlined components to achieve its goal; (i) generating paths - which denotes the creation of reference paths for trajectory by complying with the avionic performance standardizations, (ii) controlling the aircraft – which propagates the control commands by usi...
Aeroservoelastic Modelling and Analysis of a Missile Control Surface with a Nonlinear Electromechanical Actuator
Mehmet Ozan, Nalcı; Kayran, Altan (null; 2014-06-16)
In this study, aeroservoelastic modeling and analysis of a missile control surface which is operated and controlled by a power limited, nonlinear electromechanical actuator is performed. Linear models of the control fin structure and aerodynamics together with the nonlinear servo-actuation system are built and integrated. The resulting aeroservoelastic system is analyzed both in time and frequency domain. Structural model of the control fin is based on the finite element model of the fin. Aerodynamic model ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
A. Kayran, “Flight flutter testing and aeroelastic stability of aircraft,”
AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY
, pp. 494–506, 2007, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/39858.