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Aeroelastic Concepts for Flexible Wing Structures
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
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 [en]
active aeroelasticity, flexible wings, aeroelastic control, design, experiments, testing, analysis, robust, uncertainty
National Category
Mechanical Engineering
Identifiers
URN: urn:nbn:se:kth:diva-244OAI: oai:DiVA.org:kth-244DiVA: diva2:8047
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
List of papers
1. Approach to Induced Drag Reduction with Experimental Evaluation
Open this publication in new window or tab >>Approach to Induced Drag Reduction with Experimental Evaluation
2005 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 42, no 6, 1478-1485 p.Article in journal (Refereed) Published
Abstract [en]

An approach to minimize the induced drag of an aeroelastic configuration by means of multiple leading- and trailing-edge control surfaces is investigated. A computational model based on a boundary-element method is constructed and drag-reducing flap settings are found by means of numerical optimization. Further, experiments with an elastic wind-tunnel model are performed in order to evaluate the numerically obtained results. Induced-drag results are obtained by analyzing lift distributions computed from optically measured local angles of attack because standard techniques proved insufficient. Results show that significant reductions of induced drag of flexible wings can be achieved by using optimal control surface settings.

Keyword
Aeroelastic configuration; Drag reduction; Flap settings; Lift distributions
National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-7268 (URN)10.2514/1.11713 (DOI)000233846200012 ()2-s2.0-29544442463 (Scopus ID)
Note
QC 20100531. Konferens: AIAA/ASME/ASCE/AHS/ASC 45th Structures, Structural Dynamics and Materials Conference Palm Springs, CA, APR 19-22, 2004Available from: 2007-06-01 Created: 2007-06-01 Last updated: 2017-12-14Bibliographically approved
2. Analysis and Wind Tunnel Testing of a Piezoelectric Tab for Aeroelastic Control Applications
Open this publication in new window or tab >>Analysis and Wind Tunnel Testing of a Piezoelectric Tab for Aeroelastic Control Applications
2006 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, 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.

Keyword
Actuators; Aspect ratio; Electric potential; Frequency response; Numerical methods; Piezoelectricity; Wind tunnels
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-7270 (URN)10.2514/1.20060 (DOI)000242989800023 ()2-s2.0-33846068455 (Scopus ID)
Note
QC 20100713Available from: 2007-06-01 Created: 2007-06-01 Last updated: 2017-12-14Bibliographically approved
3. On the influence of modeshape variations in robust flutter analysis
Open this publication in new window or tab >>On the influence of modeshape variations in robust flutter analysis
2005 (English)Report (Other academic)
Place, publisher, year, edition, pages
Stockholm: KTH, 2005. 14 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2005:23
National Category
Mechanical Engineering
Identifiers
urn:nbn:se:kth:diva-5224 (URN)
Note
QC 20101130Available from: 2005-05-31 Created: 2005-05-31 Last updated: 2010-11-30Bibliographically approved

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Citation style
  • apa
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