Integrated Damped Fuselage Structure,
Abstract
This presentation (23 slides) describes a program, aimed at developing design guidelines for viscoelastic damping applied to skin-stringer-frame type aerospace structure. Periodic structure type response models developed as a first part of the program are discussed. Two procedures for assigning values of the damping parameters required in these models are presented. Results of test efforts to develop and verify the damping parameter assignment procedure and response prediction models are also discussed. The current status of these efforts is: (1) Response models are yielding predictions in agreement with test results; and (2) The damping parameter assignment procedures are working, but more work is needed to bring them up to the confidence level of the response models. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1984
- Accession Number
- ADP004722
Entities
People
- L. M. Butzel
Organizations
- Boeing Military Aircraft