A Fast Automatic Procedure for Flutter Clearance Assessment when in presence of Significant Structural Damage

The development of reliable and computationally efficient analysis capabilities for aeroelasticity represents one of the most intriguing challenges of our times. In this work an automatic procedure for flutter clearance assessment under damage has been set up. The whole procedure is efficient in managing flutter calculations when a stiffness or inertia change occurs in a sub-structure of the aircraft, where the change is meant to be caused by a damage occurring during flight. The efficiency is reached by means of a sub-structuring approach. The procedure has been set up on a business jet in which damage cases on a trunk of the horizontal tail are processed. The method has the advantage to be effectively used when flutter occurrence has to be evaluated in a statistical basis, because of its computational efficiency and reliability. Statistical quantities such as cumulative density function and probability density function related to flutter speed, by means of Hit or Miss Monte Carlo simulations have been calculated in order to show the potentiality of the method when approaching a stochastic analysis. It is worthwhile to highlight that the damage database which has been processed by Monte Carlo is not significant from a statistical point of view. Nevertheless the aim of the work is to set up the procedure, which is deemed a useful tool to quickly assess flutter clearance under damage, especially for military aircrafts, subjected to extent of damages which can have effects on the aeroelastic performance. It has been estimated that a statistical significant number of cases (no. 71428 cases) would require no. 80 hours of computational time with a laptop of moderate performance.

Language

  • English

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Filing Info

  • Accession Number: 01523428
  • Record Type: Publication
  • Files: TRIS, ASCE
  • Created Date: Feb 27 2014 3:01PM