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
Static and dynamic aeroelastic analysis of a very light Aircraft
Download
thesis.pdf
Date
2021-9-10
Author
Demirer, Halime Gül
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
1346
views
2301
downloads
Cite This
Aircraft design processes need to ensure that the aircraft is aeroelastically stable within its operational envelope. This thesis presents an overview of the static aeroelastic, flutter and gust response analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. The methods to be used in the aeroelastic analysis of the VLA are tested on the AGARD 445.6 wing, and the results are in good agreement with the literature. Aeroelastic model corrections such as improvement of the aerodynamic solution, examining different aerodynamic modeling and aero-structure coupling approaches are implemented. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM), which is the aerodynamic theory employed by Nastran for subsonic flows. The aerodynamic solution is improved by including the camber and the angle of incidence of the wing through the addition of an initial downwash. DLM-based loads are compared with loads obtained from computational fluid dynamics (CFD) analysis. The effects of DLM correction on the static aeroelasticity outputs are discussed. It is revealed by dynamic aeroelastic stability analysis that there is no flutter issue within the flight envelope. Matched point flutter solutions for various aileron stiffness are presented. Finally, the vertical acceleration response of the vehicle and internal structural response to the 1-cosine gust are analyzed. It is shown that the gust encountered at the cruise speed condition results in a higher vertical acceleration response than the limit maneuver load factors. Furthermore, tuned gust response analysis is conducted by tuning the gust velocity for different gust gradient lengths. Slightly higher responses than those found for the single gust gradient length required by CS-VLA [1] are captured at a shorter gradient length. Dynamic response analysis reveals that the response of the aircraft dies out in a short time and the model shows a dynamically stable behavior.
Subject Keywords
Aeroelasticity
,
Very light aircraft
,
Finite element analysis
URI
https://hdl.handle.net/11511/93190
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Static and Dynamic Aeroelastic Analysis of a Very Light Aircraft
Demirer, Halime Gül; Kayran, Altan (2021-09-08)
Aircraft design processes need to ensure that the aircraft will be aeroelastically stable within its operational envelope. This paper presents an overview of the static aeroelastic analysis results, flutter analysis and gust response analysis results of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM), the aerodynamic theory employed by Nastran for subsonic flows. DLM requires all lif...
COMPARATIVE STRUCTURAL OPTIMIZATION STUDY OF COMPOSITE AND ALUMINUM HORIZONTAL TAIL PLANE OF A HELICOPTER
Arpacıoğlu, Bertan; Kayran, Altan (2019-11-11)
This work presents structural optimization studies of aluminum and composite material horizontal tail plane of a helicopter by using MSC. NASTRAN SOL200 optimization capabilities. Structural design process starts from conceptual design phase, and structural layout design is performed by using CATIA. In the preliminary design phase, study focuses on the minimum weight optimization with multiple design variables and similar constraints for both materials. Aerodynamic load calculation is performed using ANSYS ...
Determination of dynamically equivalent fe models of aircraft structures by using modal test data
Karaağaçlı, Taylan; Özgüven, Hasan Nevzat; Yıldız, Erdinç N.; Department of Mechanical Engineering (2010)
Reliable flutter analysis of aircraft structures is a major requirement to determine safe flight envelops. Dynamically equivalent finite element model of an aircraft structure correlating well with experimental modal is a major requirement for a reliable flutter analysis. Currently available model updating techniques require enormous time and engineering work to achieve appropriate finite element models of aircraft structures. The method developed within the scope of this thesis work aims to remove importan...
Flight flutter testing and aeroelastic stability of aircraft
Kayran, Altan (2007-01-01)
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.
Generic trim analysis and simulation algorithm creation for design and optimization of the fixed wing aircraft
Özdemir, Mustafa; Kurtuluş, Dilek Funda (2021-09-10)
In order to design a fixed wing aircraft, certain phases are needed to perform. From these phases, trim analysis and simulation are very crucial for design process. Trim and simulation analysis enable to calculate performance and stability characteristics of the aircraft. After aerodynamic, weight and engine database creation, the next step is trim analysis and simulations. However, database creation phase requires a huge amount of computing time, and for the preliminary design phase it is needed to perform...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
H. G. Demirer, “Static and dynamic aeroelastic analysis of a very light Aircraft,” M.S. - Master of Science, Middle East Technical University, 2021.