A multi-fidelity, multi-disciplinary analysis and optimization framework for the design of morphing UAV wings

Date

2015-01-01

Author

Ciarella, Andrea
Tsotskas, Christos
Hahn, Marco
Werter, Noud P. M.
De Breuker, Roeland
Beaverstock, Chris S.
Friswell, Michael I.
Yang, Yosheph
Özgen, Serkan
Antoniadis, Antonios
Tsoutsanis, Panagiotis
Drikakis, Dimitris

Metadata

Show full item record

Item Usage Stats

200
views

0
downloads

© 2015 American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.A framework for the design and optimization of a morphing wing is presented. It allows the user to simplify the design process of a morphing UAV wing with a simple and effective interface with the possibility to easily switch between flight phases and morphing concepts. It consists of two main solvers: a high-fidelity CFD module for detailed RANS simulation and a fast low-fidelity module that solves the aeroelastic problem by coupling a geometrically nonlinear structural model to a potential flow aerodynamic model. The structure of the framework and the methodology used for the design of a morphing UAV wing are detailed. This wing is the focus of the European FP7 CHANGE project and serves as an example of the application of this methodology.

Subject Keywords

Aeroelasticity, Computational fluid dynamics, Design

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84960346827&origin=inward
https://hdl.handle.net/11511/88394

Conference Name

16th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 2015, (22 - 26 Haziran 2015)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Implementation of ball-center spring analogy mesh deformation technique with CFD design optimization Yang, Yosheph; Özgen, Serkan (2015-01-01) © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Mesh deformation technique plays an important role in several numerical simulations and applications including design optimization. This paper aims to implement the developed unstructured mesh deformation technique for CFD Design Optimization around 2-D Airfoils. During the optimization procedure, the newly deformed mesh is generated by using the updated Ball-Center Spring analogy mesh deformation technique. The compar...
A modeling and simulation tool for safe store separation envelope generation using monte carlo simulations Unal, Kenan; Baran, Özgür Uğraş (2018-01-01) © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.When an air released store is developed or undergoes substantial updates, integration to aircraft is realized through a certification process. One of the most important steps of the certification process is to determine safe separation envelope. For this process there are several approaches: full scale flight tests, computational fluid dynamics (CFD) simulation techniques and wind tunnel captive trajectory tests. Separ...
A computational study of flow separation characteristics and wake profiles behind a flapping airfoil Tuncer, İsmail Hakkı (1999-01-01) © 1999 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.Unsteady, viscous flowfields over a NACA0012 airfoil oscillated in plunge and/or pitch at various reduced frequency, amplitude and phase shift are computed. Vortical wake formations, boundary layer flows at the leading edge, the formation of leading edge vortices and their downstream convection are presented in terms of unsteady particle traces. Flow separation characteristics and thrust producing wake profiles are identifie...
A viscous-inviscid interaction method for 2-D unsteady, compressible flows Tuncer, İsmail Hakkı; Platzer, Max F. (1993-01-01) © 1993 American Institute of Aeronautics and Aerodynamics, Inc. All rights reserved.A Navier-Stokes/potential flow interactive solution method suitable for the solution of steady-state and unsteady flowfields around airfoils has been developed. The Navier-Stokes equations are solved in the close proximity of an airfoil and in its wake. The inviscid flowfield surrounding the viscous flow regions is assumed to be irrotational and isentropic. In the inviscid flow region, the potential flow equations, which are...
Structural dynamics analysis and passive control of wind turbine vibrations with tuned mass damper (TMD) technique Farsadi, Touraj; Kayran, Altan (2016-01-01) © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.This paper investigates the use of a passive control device, tuned mass damper (TMD) for the control of vibrations of a simplified wind turbine. In the wind turbine model, tower and blades are modeled with continuous beam structure. Concentrated mass is considered as the nacelle. TMD system is placed at top of tower and attached to the nacelle. The coupled governing equation of motions and associated boundary condition...

Citation Formats

A. Ciarella et al., “A multi-fidelity, multi-disciplinary analysis and optimization framework for the design of morphing UAV wings,” Texas, Amerika Birleşik Devletleri, 2015, Accessed: 00, 2021. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84960346827&origin=inward.