Composite buckling analysis using discrete damage modeling J. Scott McQuien * and Endel V. Iarve † University of Texas at Arlington Research Institute, Fort Worth, Texas, 76118 David H. Mollenhauer ‡ Air Force Research Laboratory, Wright Patterson AFB, Ohio, 45433-7750, USA Michael Braginsky § and Michael Stuebner § University of Dayton Research Institute, Dayton, Ohio, 45469 A Total-Lagrange formulation for geometric nonlinearity was implemented within the Rx- FEM framework. Rx-FEM is a discrete damage modeling method for progressive damage analysis which introduces displacement discontinuities to represent matrix cracks and de- laminations in composite materials. The effects of geometric nonlinearity on other Rx-FEM material nonlinearities were then demonstrated by leveraging the formulation against a two- cell frame demonstration problem. Geometric nonlinearity was shown to enable the simulation of buckling of the composite laminate, which was significantly influenced by the presence and growth of matrix cracks. I. Introduction G nonlinearity plays an essential role in the accurate analysis of damage evolution in buckling or post-buckled composite laminates. The Regularized-Extended Finite Element Method (Rx-FEM) is a discrete damage modeling (DDM) progressive damage analysis (PDA) method which models the initiation and propagation of delaminations and matrix cracks within a composite laminate [1], and has been demonstrated at the coupon level in static and fatigue [2, 3] and at the element level [4]. Until recently, Rx-FEM was limited to a geometrically linear finite element formulation with several modes of material nonlinearity. These nonlinearities included cohesive zones as part of the mesh independent cracking model (MIC), and continuum damage stiffness degradation for progressive fiber failure. In order to leverage Rx-FEM analysis capability in the damage analysis of buckling or post-buckled composite laminates, for the first time, a Total Lagrangian (TL) formulation for isoparametric finite elements was implemented into the Rx-FEM framework, which allows for the analysis of configurations that may undergo large displacements or rotations. In this work, the geometrically nonlinear Rx-FEM formulation is demonstrated on a two-cell frame configuration for purposes of investigating the effects of considering geometric nonlinearity in addition to the aforementioned material nonlinearities. The discussion will begin with a brief overview of the Rx-FEM formulation, and the implementation of the TL formulation within its framework. The two-cell frame configuration will then be detailed and analysis results presented. II. Theory This section will provide a description of the implementation of Rx-FEM used in this work. Features of the implementation relevant to the current work will be described as well as usage and the overall modeling approach of the code. Then a cursory review of the MIC theory will be offered. Lastly, the formulation for geometric nonlinearity will be briefly discussed. A. Rx-FEM implementation overview Rx-FEM is a regularized-extended finite element formulation built around the mesh independent cracking (MIC) damage model. In short, MIC is a method which allows for the insertion of cracks independent of the finite element discretization * Research Engineer, UTARI/IPPM, 7300 Jack Newell Blvd. S, Non-Member. † Professor, Department of Mechanical and Aerospace Engineering and UTARI/IPPM, 7300 Jack Newell Blvd. S, Member. ‡ Senior Research Engineer, AFRL/RX, Composites Branch, 2941 Hobson Way/AFRL/RXBC, Non-Member. § Research Engineer, UDRI, 300 College Park Avenue, Non-Member. 1 Downloaded by Hari Adluru on January 17, 2019 | http://arc.aiaa.org | DOI: 10.2514/6.2019-2386 AIAA Scitech 2019 Forum 7-11 January 2019, San Diego, California 10.2514/6.2019-2386 Copyright © 2019 by the American Institute of Aeronautics and Astronautics, Inc. The U.S. Government has a royalty-free license to exercise all rights under the copyright claimed herein for Governmental purposes. All other rights are reserved by the copyright owner. AIAA SciTech Forum
Composite buckling analysis using discrete damage modeling
May 17, 2023
Welcome message from author
This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
Related Documents
