Proceedings Vol. 23 (2017)
ENGINEERING MECHANICS 2017
May 15 – 18, 2017, Svratka, Czech Republic
Copyright © 2017 Brno University of Technology, Faculty of Mechanical Engineering, Institute of Solid Mechanics, Mechatronics and Biomechanics, Brno
ISSN 1805-8248 (printed)
ISSN 1805-8256 (electronic)
list of papers scientific commitee
pages 234 - 237, full text
This 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.
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