Buckling and post-buckling analysis of cracked stiffened panels via an X-Ritz method

Risultato della ricerca: Article

4 Citazioni (Scopus)

Abstract

A multi-domain eXtended Ritz formulation, called X-Ritz, for the analysis of buckling and post-buckling of stiffened panels with cracks is presented. The theoretical framework is based on the First-order Shear Deformation Theory and accounts for von Kármán's geometric nonlinearities. The structure is modeled as assembly of plate elements. Penalty techniques are used to fulfill the continuity condition along the edges of contiguous elements and to satisfy essential boundary conditions requirements. The use of an extended set of approximating functions allows to model through-the-thickness cracks and to capture the crack opening and tip singular fields as well as the structural behavior within each single domain. Numerical results for buckling and post-buckling of cracked stiffened panels are compared with finite elements simulations and literature solutions, showing the accuracy and potential of the proposed approach.
Lingua originaleEnglish
pagine (da-a)268-282
Numero di pagine15
RivistaAerospace Science and Technology
Volume86
Stato di pubblicazionePublished - 2019

Fingerprint

Buckling
Cracks
Shear deformation
Boundary conditions

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cita questo

@article{10fbcda7bba14c6fb143ca630ed0c3e6,
title = "Buckling and post-buckling analysis of cracked stiffened panels via an X-Ritz method",
abstract = "A multi-domain eXtended Ritz formulation, called X-Ritz, for the analysis of buckling and post-buckling of stiffened panels with cracks is presented. The theoretical framework is based on the First-order Shear Deformation Theory and accounts for von K{\'a}rm{\'a}n's geometric nonlinearities. The structure is modeled as assembly of plate elements. Penalty techniques are used to fulfill the continuity condition along the edges of contiguous elements and to satisfy essential boundary conditions requirements. The use of an extended set of approximating functions allows to model through-the-thickness cracks and to capture the crack opening and tip singular fields as well as the structural behavior within each single domain. Numerical results for buckling and post-buckling of cracked stiffened panels are compared with finite elements simulations and literature solutions, showing the accuracy and potential of the proposed approach.",
keywords = "Aerospace Engineering, Buckling, Cracks, Post-buckling, Stiffened panels, Thin-walled structures, X-Ritz method",
author = "Alberto Milazzo and Vincenzo Gulizzi and Oliveri",
year = "2019",
language = "English",
volume = "86",
pages = "268--282",
journal = "Aerospace Science and Technology",
issn = "1270-9638",
publisher = "Elsevier Masson SAS",

}

TY - JOUR

T1 - Buckling and post-buckling analysis of cracked stiffened panels via an X-Ritz method

AU - Milazzo, Alberto

AU - Gulizzi, Vincenzo

AU - Oliveri, null

PY - 2019

Y1 - 2019

N2 - A multi-domain eXtended Ritz formulation, called X-Ritz, for the analysis of buckling and post-buckling of stiffened panels with cracks is presented. The theoretical framework is based on the First-order Shear Deformation Theory and accounts for von Kármán's geometric nonlinearities. The structure is modeled as assembly of plate elements. Penalty techniques are used to fulfill the continuity condition along the edges of contiguous elements and to satisfy essential boundary conditions requirements. The use of an extended set of approximating functions allows to model through-the-thickness cracks and to capture the crack opening and tip singular fields as well as the structural behavior within each single domain. Numerical results for buckling and post-buckling of cracked stiffened panels are compared with finite elements simulations and literature solutions, showing the accuracy and potential of the proposed approach.

AB - A multi-domain eXtended Ritz formulation, called X-Ritz, for the analysis of buckling and post-buckling of stiffened panels with cracks is presented. The theoretical framework is based on the First-order Shear Deformation Theory and accounts for von Kármán's geometric nonlinearities. The structure is modeled as assembly of plate elements. Penalty techniques are used to fulfill the continuity condition along the edges of contiguous elements and to satisfy essential boundary conditions requirements. The use of an extended set of approximating functions allows to model through-the-thickness cracks and to capture the crack opening and tip singular fields as well as the structural behavior within each single domain. Numerical results for buckling and post-buckling of cracked stiffened panels are compared with finite elements simulations and literature solutions, showing the accuracy and potential of the proposed approach.

KW - Aerospace Engineering

KW - Buckling

KW - Cracks

KW - Post-buckling

KW - Stiffened panels

KW - Thin-walled structures

KW - X-Ritz method

UR - http://hdl.handle.net/10447/339987

M3 - Article

VL - 86

SP - 268

EP - 282

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

SN - 1270-9638

ER -