Structural and aeroelastic flutter analysis of wing store systems and structural modification approach in aeroelasticity

Download

index.pdf

Date

2021-9-08

Author

Akpınar, Aytaç

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

930
views

2154
downloads

The preliminary aeroelastic design process of the wings with stores is one of the most significant design activities to be considered in the aerospace industry. The focus of this thesis is mainly based on the dynamic aeroelasticity of the wing store systems including the discipline of mechanical vibrations. In the present study, the Finite Element Method (FEM) and structural modification approach are primarily implemented in the wing store aeroelastic systems. Aero-structural modeling and aeroelastic flutter analysis of the wing store systems are performed for 1-D beam-like and 2-D delta wings. A lumped mass store model is introduced to beam-like wings while a 1-DOF pitching elastic store model is introduced for delta wings. The structural model for the wing store systems is defined through the Finite Element Method (FEM) and store attachment is considered as local structural modifications. The structural and aeroelastic flutter characteristics of beam-like wings and delta wings with stores are investigated including different types of flutter solution methods, namely, K-Method, P-K Method, and Non-Iterative P-K Method. The traditional redesign process of the aeroelastic model is redefined by introducing the Dual Modal Structural Modification (DMSM) method as aeroelastic systems are concerned. The design optimization study for the store parameters is carried out considering the worst-case flutter criteria. This thesis includes different types of solution methods that are developed in-house and by utilizing commercial software.

Subject Keywords

Wing store flutter, Structural modification, Store design optimization

URI

https://hdl.handle.net/11511/93263

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Structural and aeroelastic analyses of a composite tactical unmanned air vehicle Özöztürk, Sedat; Kayran, Altan; Tamer, Aykut; Department of Aerospace Engineering (2011) In this thesis, computational aerodynamics, structural and aeroelastic analyses of the composite tactical unmanned air vehicle which is designed and manufactured in the Department of Aerospace Engineering are performed. Verification of the structural integrity of the air vehicle is shown at the minimum maneuvering and the dive speeds at the static limit loads which are calculated by the computational aerodynamics analysis of the full aircraft model. In the current work, aerodynamic loads are re-calculated f...
Design, analysis and optimization of thin walled semi-monocoque wing structures using different structural idealization in the preliminary design phase Dababneh, Odeh; Kayran, Altan (2014-01-01) In modeling an aircraft wing, structural idealizations are often employed in hand calculations to simplify the structural analysis. In real applications of structural design, analysis and optimization, finite element methods are used because of the complexity of the geometry, combined and complex loading conditions. The purpose of this paper is to give a comprehensive study on the effect of using different structural idealizations on the design, analysis and optimization of thin walled semi-monocoque wing s...
Structural and aerodynamic analyses of a hybrid trailing edge control surface of a fully morphing wing Gürses, Ercan; Yang, Yosheph; Arslan, Pinar; Kalkan, Ugur; Tıraş, Harun; Şahin, Melin; Özgen, Serkan; Yaman, Yavuz (2017-05-01) In this article, the design and analysis of a hybrid trailing edge control surface of an unmanned aerial vehicle are presented. The structural design was performed to increase and decrease the camber of the control surface to match selected airfoil profiles. The design was first analyzed with the help of finite element method to assess the morphing capability. The morphed control surface was then analyzed aerodynamically and comparisons with the original target profiles were made. According to the aerodynam...
Structural optimization of a jet trainer wing structure under strength and stiffness related constraints Adıgüzel, Ozan; Şahin, Melin; Department of Aerospace Engineering (2020-9) This thesis presents structural optimization studies for a jet trainer aircraft wing structure. The main purpose is to select the most convenient rib/spar layout for T-38 wing like geometry which consists of metallic and composite components by using a finite element modeling and analysis tool of MSC NASTRAN optimization capabilities. In this study, in order to decrease the number of design variables and as well as to be able to obtain smooth thickness transitions between adjacent zones, design variable lin...
Design and analysis of a structural component of a heavy transport aircraft Çıkrıkcı, Davut; Yaman, Yavuz; Department of Aerospace Engineering (2010) This thesis aims to present the design and analysis of a structural component of a heavy transport aircraft. The designed component is the “coupling“ which is the interface member connecting two frames or two stringers in the fuselage assembly. The “frames”, which are the circumferential stiffeners, are joined together by the “frame couplings”. The “stringers”, which are the longitudinal stiffeners, are joined together by the “stringer couplings”. At the preliminary design phase; the structural design princ...

Citation Formats

A. Akpınar, “Structural and aeroelastic flutter analysis of wing store systems and structural modification approach in aeroelasticity,” M.S. - Master of Science, Middle East Technical University, 2021.