Assessment of damage containment features of a full-scale PRSEUS fuselage panel

Bergan, Andrew C.; Bakuckas, John G.; Awerbuch, Jonathan; Tan, Tein-Min

doi:10.1016/j.compstruct.2014.03.011

Cited by 25 publications

(15 citation statements)

References 11 publications

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“…9) subjected to combined internal pressure and axial loading. [8][9][10][11] Similar favorable damage-arrest and crack-turning phenomena were observed in this test before the specimen failed at 185% of DLL in the grip region of the specimen. The large increase in loading between the initial crack growth and final panel failure load demonstrates the robust nature of the stitched interfaces and how high levels of residual panel strength can be achieved through a combination of stitching and highly tailored laminates.…”

Section: American Institute Of Aeronautics and Astronauticssupporting

confidence: 56%

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PRSEUS Structural Concept Development

Velicki

Jegley

2014

52nd Aerospace Sciences Meeting

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A lighter, more robust airframe is one of the key technological advancements necessary for the successful launch of any large next-generation transport aircraft. Such a premise dictates that considerable improvements beyond current state-of-the-art aluminum structures is needed, and that improvements of this magnitude will require an extensive use of composite materials that are not only lightweight, but also economical to produce. To address this challenge, researchers at NASA and The Boeing Company are developing a novel structural concept called the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) under the Environmentally Responsible Aviation (ERA) Project. It is an integrally stiffened panel concept that is stitched together and designed to maintain residual load-carrying capabilities under a variety of damage scenarios. In addition to improved structural performance, an important facet of this unique arrangement of stitched carbon fibers is its innovative manufacturing method that has the potential to lower fabrication costs by eliminating fasteners and autoclave cures. The rationale and development status for this new approach forms the basis of the work described in this paper. The test specimens described herein were fabricated, or are currently being fabricated, by The Boeing Company, while the structural analyses and testing tasks are being performed by NASA and Boeing personnel. Nomenclature BVID = barely visible impact damage DLL = design limit load DSD = discrete source damage DUL = design ultimate load EA = section modulus EI = section stiffness

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Section: American Institute Of Aeronautics and Astronauticssupporting

confidence: 56%

“…6) was completed. [7][8][9][10][11][12] The characteristic crack turning-and-arrest failure mode was first observed in a series of flat tension coupons with stitched and unstitched laminates ( Fig. 7).…”

Section: A Demonstrating Damage-arrest Characteristicsmentioning

confidence: 99%

PRSEUS Structural Concept Development

Velicki

Jegley

2014

52nd Aerospace Sciences Meeting

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“…The Discrete Ply Model (DPM), used in this paper, was one of the first models to use cohesive interface elements to simulate matrix cracking and delamination [46,47]. Other models of the same type exist in the literature [3,8,[48][49][50].…”

Section: Literature Reviewmentioning

confidence: 99%

Experimental and numerical analysis of Carbon Fiber Reinforced Polymer notched coupons under tensile loading

Serra

Bouvet

Castanié

et al. 2017

Composite Structures

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The behavior of composite laminates subject to notch based stress concentrations is difficult to apprehend, especially the mechanisms of damage progression leading to total failure. Numerical and experimental investigations were carried out on three different stacking sequences of notched, thin ply carbon/epoxy laminates. This paper presents a computational study of notched tensile tests (U-notch) using the Discrete Ply Modeling (DPM) method, which has already proved efficient on both in-plane and out-of-plane loading cases, such as pull through, low velocity impact and compression after impact. The specificities of this finite element model are its discrete nature (interface elements to model delamination and matrix cracks), the small number of parameters required, and its robustness. This work follows on from the study of open-hole tensile tests (same three layups) by the same authors [1] and analyzes the influence of layup and notch shape. Comparisons with experiments (using infrared technology) demonstrate that tensile strengths, and failure scenarios and patterns are predicted with acceptable accuracy.

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“…The panel design, pre-test analysis, modifications to the FASTER facility, test procedure and results have been previously published. [2][3][4][5] The purpose of this paper is to document nonlinear posttest analysis and test correlation, focusing on the global response data obtained from the curved PRSEUS panel test. In this paper the PRSEUS concept and the curved panel is described, followed by a description of the testing scenario.…”

Section: Introductionmentioning

confidence: 99%