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Closed loop roll control using aeroelastic information
KTH, Superseded Departments, Vehicle Engineering.ORCID iD: 0000-0003-2391-641X
2000 (English)In: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 4, no 7, 481-494 p.Article in journal (Refereed) Published
Abstract [en]

A mathematical model of the rolling dynamics of a flexible wing is derived by experimental measurements and 3D potential flow analysis. Based on the mathematical model which includes one aeroelastic parameter, control laws are designed which almost completely eliminate the problem of reduced aileron efficiency for increasing airspeed. Finally, the control laws are tested on the model in the wind tunnel, and good correlation with computer simulations is achieved, except when a structural mode is excited.

Place, publisher, year, edition, pages
2000. Vol. 4, no 7, 481-494 p.
Keyword [en]
aeroelasticity, controller design, nonlinear control, aileron reversal, wind tunnel testing, aircraft
Identifiers
URN: urn:nbn:se:kth:diva-20146ISI: 000165151400004OAI: oai:DiVA.org:kth-20146DiVA: diva2:338839
Note
QC 20100525Available from: 2010-08-10 Created: 2010-08-10 Last updated: 2017-12-12Bibliographically approved

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Ringertz, Ulf

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