Numerical investigation on the failure phenomena of stiffened composite panels in post-buckling regime with discrete damages.
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| Title: | Numerical investigation on the failure phenomena of stiffened composite panels in post-buckling regime with discrete damages. |
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| Authors: | Romano, F.1 f.romano@cira.it, Di Caprio, F.1, Auriemma, B.2, Mercurio, U.1 |
| Source: | Engineering Failure Analysis. Oct2015, Vol. 56, p116-130. 15p. |
| Subjects: | Failure analysis, Stiffness (Engineering), Composite materials, Mechanical buckling, Impact (Mechanics) |
| Abstract: | The aim of this work is to investigate the final failure response of damaged composite stiffened panels in post buckling regime under compressive load, by using progressive failure analysis (PFA) methodology. The selected panel is characterized by T shaped stringers and it is representative of the upper skin panel, toward the wing tip, of the wing box of a typical regional aircraft. PFA methodology has been applied in order to predict in addition to the initiation of the local failure also its propagation up to the final collapse of the panel, in presence of local damage (barely visible impact damage, BVID) and in post-buckling regime. For this purpose, discrete damages have been considered in the skin of the panel. According to the indications contained in many guidelines finalized to the preliminary design of composite structures, a simplified design model of BVID has been considered in this work, in particular a hole 1/4 in. in diameter has been used to simulate this damage. The collapse load of the panel has been evaluated considering different locations of a single damage and also considering multi-damage maps (the latter are more representative of a real damage scenario). The results of PFA presented in this work illustrate the combined effect of the reduction of the panel stiffness and of the damage propagation, and the sensitivity of the buckling onset and of the residual strength of the panel with respect to different damage locations and damage density. [ABSTRACT FROM AUTHOR] |
| Copyright of Engineering Failure Analysis is the property of Pergamon Press - An Imprint of Elsevier Science and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
| FullText | Text: Availability: 0 |
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| Header | DbId: egs DbLabel: Engineering Source An: 109552884 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Numerical investigation on the failure phenomena of stiffened composite panels in post-buckling regime with discrete damages. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Romano%2C+F%2E%22">Romano, F.</searchLink><relatesTo>1</relatesTo><i> f.romano@cira.it</i><br /><searchLink fieldCode="AR" term="%22Di+Caprio%2C+F%2E%22">Di Caprio, F.</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22Auriemma%2C+B%2E%22">Auriemma, B.</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22Mercurio%2C+U%2E%22">Mercurio, U.</searchLink><relatesTo>1</relatesTo> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Engineering+Failure+Analysis%22">Engineering Failure Analysis</searchLink>. Oct2015, Vol. 56, p116-130. 15p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Failure+analysis%22">Failure analysis</searchLink><br /><searchLink fieldCode="DE" term="%22Stiffness+%28Engineering%29%22">Stiffness (Engineering)</searchLink><br /><searchLink fieldCode="DE" term="%22Composite+materials%22">Composite materials</searchLink><br /><searchLink fieldCode="DE" term="%22Mechanical+buckling%22">Mechanical buckling</searchLink><br /><searchLink fieldCode="DE" term="%22Impact+%28Mechanics%29%22">Impact (Mechanics)</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: The aim of this work is to investigate the final failure response of damaged composite stiffened panels in post buckling regime under compressive load, by using progressive failure analysis (PFA) methodology. The selected panel is characterized by T shaped stringers and it is representative of the upper skin panel, toward the wing tip, of the wing box of a typical regional aircraft. PFA methodology has been applied in order to predict in addition to the initiation of the local failure also its propagation up to the final collapse of the panel, in presence of local damage (barely visible impact damage, BVID) and in post-buckling regime. For this purpose, discrete damages have been considered in the skin of the panel. According to the indications contained in many guidelines finalized to the preliminary design of composite structures, a simplified design model of BVID has been considered in this work, in particular a hole 1/4 in. in diameter has been used to simulate this damage. The collapse load of the panel has been evaluated considering different locations of a single damage and also considering multi-damage maps (the latter are more representative of a real damage scenario). The results of PFA presented in this work illustrate the combined effect of the reduction of the panel stiffness and of the damage propagation, and the sensitivity of the buckling onset and of the residual strength of the panel with respect to different damage locations and damage density. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Engineering Failure Analysis is the property of Pergamon Press - An Imprint of Elsevier Science and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1016/j.engfailanal.2015.03.012 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 15 StartPage: 116 Subjects: – SubjectFull: Failure analysis Type: general – SubjectFull: Stiffness (Engineering) Type: general – SubjectFull: Composite materials Type: general – SubjectFull: Mechanical buckling Type: general – SubjectFull: Impact (Mechanics) Type: general Titles: – TitleFull: Numerical investigation on the failure phenomena of stiffened composite panels in post-buckling regime with discrete damages. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Romano, F. – PersonEntity: Name: NameFull: Di Caprio, F. – PersonEntity: Name: NameFull: Auriemma, B. – PersonEntity: Name: NameFull: Mercurio, U. IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 10 Text: Oct2015 Type: published Y: 2015 Identifiers: – Type: issn-print Value: 13506307 Numbering: – Type: volume Value: 56 Titles: – TitleFull: Engineering Failure Analysis Type: main |
| ResultId | 1 |
