000021273 001__ 21273
000021273 005__ 20170522124346.0
000021273 04107 $$aeng
000021273 046__ $$k2017-05-15
000021273 100__ $$aČečrdle, J.
000021273 24500 $$aAIRCRAFT WING FLUTTER ASSESSMENT CONSIDERING DAMAGE TOLERANCE - BASED FAILURE STATES

000021273 24630 $$n23.$$pEngineering Mechanics 2017
000021273 260__ $$bBrno University of Technology, Institute of Solid Mechanics, Mechatronics and Biomechanics, Brno
000021273 506__ $$arestricted
000021273 520__ $$2eng$$aThis paper deals with aircraft wing flutter analysis considering the failure states, originated by the application of the damage - tolerance design philosophy on the wing structure. Such damages may influence the integral stiffness of a wing structure and, as a consequence, to influence its flutter characteristics. Therefore, airworthiness regulation standards require flutter analysis of these failure states. The paper presents the simple method of the wing stiffness transformation. The source model is the detailed static FE model, applicable to include the mentioned damages. Target model is the aeroelastic stick FE model, applicable for aeroelastic analyses. The method of assessment of the influence of damage on the wing flutter is shown. The methodology is demonstrated on the example of a commuter aircraft wing bending - torsional flutter. The method is applicable for compliance with FAR / CS 23.629(g)(h) requirements.

000021273 540__ $$aText je chráněný podle autorského zákona č. 121/2000 Sb.
000021273 653__ $$aAeroelasticity, Flutter, Damage Tolerance, Reglamentary Damage.

000021273 7112_ $$aEngineering Mechanics 2017$$cSvratka, CZ$$d2017-05-15 / 2017-05-18$$gEM2017
000021273 720__ $$aČečrdle, J.$$iRaška, J.
000021273 8560_ $$ffischerc@itam.cas.cz
000021273 8564_ $$s906484$$uhttps://invenio.itam.cas.cz/record/21273/files/0234.pdf$$yOriginal version of the author's contribution in proceedings, page 234, section DYN.
000021273 962__ $$r21225
000021273 980__ $$aPAPER