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Aeroelastic flutter analysis considering modeling uncertainties
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.ORCID iD: 0000-0003-1604-4262
2017 (English)In: Journal of Fluids and Structures, ISSN 0889-9746, E-ISSN 1095-8622, Vol. 74, 247-262 p.Article in journal (Refereed) Published
Abstract [en]

A method for efficient flutter analysis of aeroelastic systems including modeling uncertainties is presented. The aerodynamic model is approximated by a piece-wise continuous rational polynomial function, allowing the flutter equation to be formulated as a set of piece-wise linear eigenproblems. Feasible sets for eigenvalue variations caused by combinations of modeling uncertainties are computed with an approach based on eigenvalue differentials and Minkowski sums. The method allows a general linear formulation for the nominal system model as well as for the uncertainty description and is thus straightforwardly applicable to linearized aeroelastic models including both structural and aerodynamic uncertainties. It has favorable computational properties and, for a wide range of uncertainty descriptions, feasible sets can be computed in output polynomial time. The method is applied to analyze the flutter characteristics of a delta wing model. It is found that both structural and aerodynamic uncertainties can have a considerable effect on the damping trends of the flutter modes and thus need to be accounted for in order to obtain reliable predictions of the flutter characteristics. This indicates that it can be beneficial to allow a flexible and detailed formulation for both aerodynamic and structural uncertainties, as is possible with the present system formulation.

Place, publisher, year, edition, pages
Elsevier, 2017. Vol. 74, 247-262 p.
Keyword [en]
Flutter analysis, Modeling uncertainty, Generalized eigenproblem, Eigenvalue differential, Minkowski sum
National Category
Aerospace Engineering
Research subject
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-212048DOI: 10.1016/j.jfluidstructs.2017.06.017ISI: 000412960100015Scopus ID: 2-s2.0-85023642191OAI: oai:DiVA.org:kth-212048DiVA: diva2:1133354
Note

QC 20170816

Available from: 2017-08-15 Created: 2017-08-15 Last updated: 2017-11-02Bibliographically approved
In thesis
1. On Aerodynamic and Aeroelastic Modeling for Aircraft Design
Open this publication in new window or tab >>On Aerodynamic and Aeroelastic Modeling for Aircraft Design
2017 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

The work presented in this thesis was performed with the aim of developing improved prediction methods for aerodynamic and aeroelastic analysis to be used in aircraft design. The first part of the thesis concerns the development of a viscous-inviscid interaction model for steady aerodynamic predictions. Since an inviscid, potential flow, model already is available, the main focus is on the development of a viscous model consisting of a three-dimensional integral boundary layer model. The performance of the viscous-inviscid interaction model is evaluated and it is found that the accuracy of the predictions as well as the computational cost appear to be acceptable for the intended application. The presented work also includes an experimental study aimed at analyzing steady and unsteady aerodynamic characteristics of a laminar flow wing model. An enhanced understanding of these characteristics is presumed to be useful for the development of improved aerodynamic prediction models. A combination of nearly linear as well as clearly nonlinear aerodynamic variations are observed in the steady as well as in the unsteady experimental results and it is discussed how these may relate to boundary layer properties as well as to aeroelastic stability characteristics. Aeroelastic considerations are receiving additional attention in the thesis, as a method for prediction of how flutter characteristics are affected by modeling uncertainties is part of the presented material. The analysis method provides an efficient alternative for obtaining increased information about, as well as enhanced understanding of, aeroelastic stability characteristics.

Place, publisher, year, edition, pages
KTH Royal Institute of Technology, 2017. 27 p.
Series
TRITA-AVE, ISSN 1651-7660 ; 2017:44
Keyword
viscous-inviscid interaction model, laminar flow wing, aerodynamics, aeroelasticity, aircraft design
National Category
Engineering and Technology
Research subject
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-212051 (URN)978-91-7729-480-1 (ISBN)
Public defence
2017-09-22, F3, Lindstedtsvägen 26, Stockholm, 14:00 (English)
Opponent
Supervisors
Note

QC 20170816

Available from: 2017-08-16 Created: 2017-08-15 Last updated: 2017-08-16Bibliographically approved

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