Nonlinear Static Aeroelastic Behavior of Composite Missile Fin with Interlaminar and Intralaminar Damage

Özkaya, Özge; Kayran, Altan

doi:10.2514/6.2018-1449

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2018

DOI: 10.2514/6.2018-1449

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Nonlinear Static Aeroelastic Behavior of Composite Missile Fin with Interlaminar and Intralaminar Damage

Özge Özkaya¹,

Altan Kayran

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2019

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“…For this purpose, 3-D finite element models of composite missile wings in different positions were prepared. In this thesis, ANSYS CFX was used for the fluid model (CFD) and ANSYS Mechanical was used for the structural model (FEM)[44].…”

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Aeroelastic Modeling and Analysis of High Aspect Ratio Wings With Different Fidelity Structural Models

Çiçek

Kayran

2019

Volume 1: Advances in Aerospace Technology

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This paper is concerned with the aeroelastic modeling and analysis of high aspect ratio wings with large torsional deflections with different fidelity structural models. The approach for structural modeling presented here is based on linear and nonlinear theories. The linear theories are based on the slender-straight wing and bending-torsion beam finite element formulations. The nonlinear theory is based on the nonlinear finite element model with only a torsional rotation degree of freedom to study the static aeroelastic behavior. The aerodynamic theory used for aeroelastic coupling is ESDU 95010 [1], which uses steady lifting-surface theory based on Multhopp-Richardson’s solution to provide the spanwise loading of lifting surfaces with camber and twist. Analyses are performed with three different structural models coupled with ESDU for simple plate-like wing models. The results of linear structural models are verified with MSC NASTRAN® and the nonlinear structural model results are verified with the work of Trahair [2]. Linear aeroelastic models are compared with the MSC NASTRAN® solution performed by SOL144. Significant differences in torsional deflection of tip location are observed between the linear and the nonlinear solution methodologies. The linear theory is found to be conservative for the aeroelastic analysis of high aspect ratio wings.

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confidence: 99%

Aeroelastic Modeling and Analysis of High Aspect Ratio Wings With Different Fidelity Structural Models

Çiçek

Kayran

2019

Volume 1: Advances in Aerospace Technology

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Nonlinear Static Aeroelastic Behavior of Composite Missile Fin with Interlaminar and Intralaminar Damage

Cited by 1 publication

References 5 publications

Aeroelastic Modeling and Analysis of High Aspect Ratio Wings With Different Fidelity Structural Models

Aeroelastic Modeling and Analysis of High Aspect Ratio Wings With Different Fidelity Structural Models

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