AIRCRAFT WING FLUTTER ASSESSMENT CONSIDERING DAMAGE TOLERANCE - BASED FAILURE STATES

Abstract eng:
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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