Change search
ReferencesLink to record
Permanent link

Direct link
Design and Testing of Flexible Aircraft Structures
KTH, Superseded Departments, Aeronautical and Vehicle Engineering.
2004 (English)Doctoral thesis, comprehensive summary (Other scientific)
Abstract [en]

Methods for structural design, control, and testing offlexible aircraft structures are considered. Focus is onnonconventional aircraft con- figurations and control concepts.The interaction between analysis and testing is a central topicand all studies include validation testing and comparisonbetween computational and experimental results.

The first part of the thesis is concerned with the designand testing of an aeroelastic wind-tunnel model representing aBlended Wing Body (BWB) aircraft. The investigations show thata somewhat simplified wind-tunnel model design concept isuseful and efficient for the type of investigations considered.Also, the studies indicate that well established numericaltools are capable of predicting the aeroelastic behavior of theBWB aircraft with reasonable accuracy. Accurate prediction ofthe control surface aerodynamics is however found to bedifficult.

A new aerodynamic boundary element method for aeroelastictimedomain simulations and its experimental validation arepresented. The properties of the method are compared totraditional methods as well as to experimental results. Thestudy indicates that the method is capable of efficient andaccurate aeroelastic simulations.

Next, a method for tailoring a structure with respect to itsaeroelastic behavior is presented. The method is based onnumerical optimization techniques and developed for efficientdesign of aeroelastic wind-tunnel models with prescribed staticand dynamic aeroelastic properties. Experimental validationshows that the design method is useful in practice and that itprovides a more efficient handling of the dynamic aeroelasticproperties compared to previous methods.

Finally, the use of multiple control surfaces andaeroelastic effects for efficient roll maneuvering isconsidered. The idea is to design a controller that takesadvantage of the elasticity of the structure for performancebenefits. By use of optimization methods in combination with afairly simple control system, good maneuvering performance isobtained with minimal control effort. Validation testing usinga flexible wind-tunnel model and a real-time control systemshows that the control strategy is successful in practice.Keywords: aeroelasticity, active aeroelastic structures,aeroelastic tailoring, control, structural optimization,wind-tunnel testing.

Place, publisher, year, edition, pages
Stockholm: Farkost och flyg , 2004. , 33 p.
Trita-AVE, ISSN 1651-7660 ; 2004:14
Keyword [en]
aeroelasticity, active aeroelastic structures, aeroelastic tailoring, control, structural optimization, wind-tunnel testing
National Category
Aerospace Engineering
URN: urn:nbn:se:kth:diva-3761ISBN: 91-7283-753-5OAI: diva2:9611
Public defence
2004-05-28, 00:00
QC 20120320Available from: 2004-05-27 Created: 2004-05-27 Last updated: 2012-03-20Bibliographically approved

Open Access in DiVA

fulltext(825 kB)10161 downloads
File information
File name FULLTEXT01.pdfFile size 825 kBChecksum SHA-1
Type fulltextMimetype application/pdf

Search in DiVA

By author/editor
Carlsson, Martin
By organisation
Aeronautical and Vehicle Engineering
Aerospace Engineering

Search outside of DiVA

GoogleGoogle Scholar
Total: 10161 downloads
The number of downloads is the sum of all downloads of full texts. It may include eg previous versions that are now no longer available

Total: 1170 hits
ReferencesLink to record
Permanent link

Direct link