Integral passive damping for aircraft fuselage structure

Salvatore L. Liguore; Theodor H. Beier; Bradley R. Allen; Michael L. Zeigler

doi:10.1117/12.208909

5 May 1995 Integral passive damping for aircraft fuselage structure

Salvatore L. Liguore, Theodor H. Beier, Bradley R. Allen, Michael L. Zeigler

Proceedings Volume 2445, Smart Structures and Materials 1995: Passive Damping; (1995) https://doi.org/10.1117/12.208909
Event: Smart Structures and Materials '95, 1995, San Diego, CA, United States

Abstract

This paper describes the development of damped structure for the Supportable Technology for Affordable Fighter Structures (STAFS) Program. The study started with analytical design trade studies and progressed through a series of tests to characterize adhesive behavior, performance testing of a component level integrally damped panel concept, and full scale design integration. Analyses were performed on finite element panel models with viscoelastic elements in the bond areas to determine the sensitivities of configuration and adhesive type to overall damping achieved. The concepts studied showed that as much as 10 percent structural damping could be obtained in the structural modes of interest. Test panels with and without damping treatments were fabricated using super plastically formed-adhesive bonded 2095 aluminum, and tested to measure the comparative response improvement in the damped panels. A substantial weight savings was realized in comparison to the monolithic metal panels which would be required to withstand the acoustic environment.

Citation Download Citation

Salvatore L. Liguore, Theodor H. Beier, Bradley R. Allen, and Michael L. Zeigler "Integral passive damping for aircraft fuselage structure", Proc. SPIE 2445, Smart Structures and Materials 1995: Passive Damping, (5 May 1995); https://doi.org/10.1117/12.208909

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