Laminated Damped Fuselage Structures,
Abstract
This paper discusses the application of constrained layer damping, in the form of laminated skins, frames, and equipment racks, to control of acoustical fatigue of structures and vibration of equipment in the aft fuselage sections of large aircraft. Discussions of applications of constrained layer damping go beyond conventional skin-stringer configurations to include honeycomb structures. It is shown that the influence of constrained layer damping on the response of a honeycomb panel at its critical frequency is very different from the influences on its resonant responses. A discussion of baseline data and background methodology includes laboratory characterization of materials, acoustical fatigue tests of baseline and laminated structures, peculiarities of structures with high damping, influences of various boundary conditions on damped panels, dynamic versus static stiffness of damped panels, and comparisons of predicted and measured stresses in damped and undamped panels that are representative of aircraft structures. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1984
- Accession Number
- ADP004720
Entities
People
- R. A. Ely