Presentation
An Analysis Methodology to Predict Damage Propagation in Notched Composite Fuselage Structures
Society for the Advancement of Material and Process Engineering Conference and Exhibition (SAMPE 2015) (2015)
20 May 2015
Abstract
A new methodology is proposed for predicting damage propagation in notched composite skin-stiffened structures. The proposed approach considers the interaction of damage propagation in the skin with delamination of the stiffener in order to assess the damage containment behavior of the structure. The damage propagating from a notch within a thin fiber-reinforced polymer skin is idealized as a through-the-thickness cohesive crack. The cohesive law for the through-the-thickness crack is characterized using a compact tension test. The approach was applied to a full-scale pultruded rod stitched efficient unitized structure (PRSEUS) concept fuselage panel that was tested recently. The stitched skin/stringer interfaces, a key feature of the PRSEUS concept, were modeled to assess the effectiveness of the stitching at containing damage propagation. Comparison between the predicted and observed damage extension shows acceptable agreement throughout loading. These results indicate that the model can represent accurately the complex interactions between a through-the-thickness crack in the skin and delamination between the skin and stringer. The model is used to demonstrate that the skin-stiffener interface toughness is critical to damage containment capability
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Details
- Title
- An Analysis Methodology to Predict Damage Propagation in Notched Composite Fuselage Structures
- Creators
- A. Bergan - NASA Langley Research CenterC. Davila - NASA Langley Research CenterF. Leone - NASA Langley Research CenterJ. Awerbuch - Drexel UniversityT.-M. Tan - Drexel University
- Conference
- Society for the Advancement of Material and Process Engineering Conference and Exhibition (SAMPE 2015) (2015)
- Publisher
- Langley Research Center
- Resource Type
- Presentation
- Language
- English
- Academic Unit
- Mechanical Engineering and Mechanics
- Identifiers
- 991019173435404721