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Assessment of Critical Fuel Configurations Using Robust Flutter Analysis
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2007 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 44, no 6, 2034-2039 p.Article in journal (Refereed) Published
Abstract [en]

An approach to assess critical fuel configurations using robust flutter analysis is presented. A realistic aircraft model is considered to demonstrate how an available finite element model can be adapted to easily apply robust flutter analysis with respect to structural variations such as fuel-level variations. The study shows that standard analysis tools can be used to efficiently generate the system data that are required to perform robust flutter analysis. The μ-k method is used to compute the worst-case flutter speed, and the corresponding worst-case fuel configuration is found. The main advantage of the proposed approach is that μ. analysis guarantees robustness with respect to all possible fuel configurations represented by the tank model.

Place, publisher, year, edition, pages
2007. Vol. 44, no 6, 2034-2039 p.
Keyword [en]
Aircraft; Finite element method; Robust control; Statistical methods; Fuel configurations; Standard analysis tools; Tank models; Flutter (aerodynamics)
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-7272DOI: 10.2514/1.30500ISI: 000251703900028Scopus ID: 2-s2.0-38149030900OAI: oai:DiVA.org:kth-7272DiVA: diva2:12231
Note
QC 20100713. Uppdaterad från Submitted till Published 20100713. Konferens: AIAA/ASME/ASCE/AHS/ASC 47th Structures, Structural Dynamics, and Materials Conference, Newport, RI, MAY 01-04, 2006.Available from: 2007-06-01 Created: 2007-06-01 Last updated: 2017-12-14Bibliographically approved
In thesis
1. Aeroelastic Concepts for Flexible Aircraft Structures
Open this publication in new window or tab >>Aeroelastic Concepts for Flexible Aircraft Structures
2007 (English)Doctoral thesis, comprehensive summary (Other scientific)
Abstract [en]

In this thesis, aeroelastic concepts for increased aircraft performance are developed and evaluated. Active aeroelastic concepts are in focus as well as robust analysis concepts aiming at efficient analysis using numerical models with uncertain or varying model parameters.

The thesis presents different approaches for exploitation of fluid-structure interaction of active aeroelastic structures. First, a high aspect ratio wing in wind tunnel testing conditions is considered. The wing was developed within the European research project \textit{Active Aeroelastic Aircraft Structures} and used to demonstrate how structural flexibility can be exploited by using multiple control surfaces such that the deformed wing shape gives minimum drag for different flight conditions. Two different drag minimization studies are presented, one aiming at reduced induced drag based on numerical optimization techniques, another one aiming at reduced measured total drag using real-time optimization in the wind tunnel experiment. The same wing is also used for demonstration of an active concept for gust load alleviation using a piezoelectric tab. In all studies on the high aspect ratio wing, it is demonstrated that structural flexibility can be exploited to increase aircraft performance.

Other studies in this thesis investigate the applicability of robust control tools for flutter analysis considering model uncertainty and variation. First, different techniques for taking large structural variations into account are evaluated. Next, a high-fidelity numerical model of an aircraft with a variable amount of fuel is considered, and robust analysis is applied to find the worst-case fuel configuration. Finally, a study investigating the influence of uncertain external stores aerodynamics is presented. Overall, the robust approach is shown to be capable of treating large structural variations as well as modeling uncertainties to compute worst-case configurations and flutter boundaries.

Place, publisher, year, edition, pages
Stockholm: KTH, 2007. 31, 24, 16, 16, 16, 23 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2007:29
Keyword
aeroelasticity, active aeroelastic aircraft structures, aeroelastic control, wind-tunnel testing, flutter analysis, robust flutter analysis, worst-case configuration
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-4419 (URN)978-91-7178-706-4 (ISBN)
Public defence
2007-06-15, F3, Lindstedtsvägen 26, Stockholm, 13:15
Opponent
Supervisors
Note
QC 20100713Available from: 2007-06-01 Created: 2007-06-01 Last updated: 2010-07-13Bibliographically approved

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