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Analysis and Wind Tunnel Testing of a Piezoelectric Tab for Aeroelastic Control Applications
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
Technion - Israel Institute of Technology.
2006 (English)In: Journal of Aircraft, ISSN 0021-8669, Vol. 43, no 6, 1799-1804 p.Article in journal (Refereed) Published
Abstract [en]

A concept for exploitation of a piezoelectric actuator by using aeroelastic amplification is presented. The approach is to use the actuator for excitation of a tab that occupies the rear 25 % of a free-floating trailing edge flap. A flexible high aspect ratio wing wind tunnel model is used as a test case. Wind tunnel experiments were performed to determine frequency response functions for validation of the numerical model used for the control law design. The aeroservoelastic model is based on state-space equations of motion that accept piezoelectric voltage commands. Control laws are derived for gust alleviation with flutter and control authority constraints, and numerical results that demonstrate a significant reduction in the structural response are presented. Possible applications and feasibility of the concept are discussed.

Place, publisher, year, edition, pages
2006. Vol. 43, no 6, 1799-1804 p.
Keyword [en]
Actuators; Aspect ratio; Electric potential; Frequency response; Numerical methods; Piezoelectricity; Wind tunnels
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-7270DOI: 10.2514/1.20060ISI: 000242989800023Scopus ID: 2-s2.0-33846068455OAI: oai:DiVA.org:kth-7270DiVA: diva2:12229
Note
QC 20100713Available from: 2007-06-01 Created: 2007-06-01 Last updated: 2010-07-13Bibliographically 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
2. Aeroelastic Concepts for Flexible Wing Structures
Open this publication in new window or tab >>Aeroelastic Concepts for Flexible Wing Structures
2005 (English)Licentiate thesis, comprehensive summary (Other scientific)
Abstract [en]

This thesis summarizes investigations performed within design, analysis and experimental evaluation of flexible aircraft structures. Not only the problems, but rather the opportunities related to aeroelasticity are discussed.

In the first part of the thesis, different concepts for using active aeroelastic configurations to increase aircraft performance are considered. In particular, one study deals with the minimization of the induced drag of a highly flexible wing by using multiple control surfaces. Another study deals with a possible implementation of a high-bandwidth piezo electric actuator for control applications using aeroelastic amplification.

The second part of the thesis deals with the development of an approach for modeling and analysis of flexible structures considering uncertainties in analysis models. Especially in cases of large structural variations, such as fuel level variations, a fixed-base modal formulation in robust flutter analysis may lead to incorrect results. Besides a discussion about this issue, possible means of treating this problem are presented.

Place, publisher, year, edition, pages
Stockholm: KTH, 2005. 25 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2005:22
Keyword
active aeroelasticity, flexible wings, aeroelastic control, design, experiments, testing, analysis, robust, uncertainty
National Category
Mechanical Engineering
Identifiers
urn:nbn:se:kth:diva-244 (URN)
Presentation
2005-06-10, S40, Teknikringen 8, 10:00
Opponent
Supervisors
Note
QC 20101130Available from: 2005-05-31 Created: 2005-05-31 Last updated: 2010-12-06Bibliographically approved

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