The Experts below are selected from a list of 168 Experts worldwide ranked by ideXlab platform

Satya N Atluri - One of the best experts on this subject based on the ideXlab platform.

  • Residual strength prediction for aircraft panels with Multiple Site Damage, using the "EPFEAM" for stable crack growth analysis
    Computational Mechanics, 1995
    Co-Authors: C. R. Pyo, Hiroshi Okada, Satya N Atluri
    Abstract:

    190 Abstract In this paper, a new analytical method for solving stable crack propagation problems in a ductile panel with a row of cracks, is presented. The main purpose of the present study is to estimate the maximum load carrying capacity of such panels accurately. The so called Elastic Plastic Finite Element Alternating Method (Pyo et al. (1994)) was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stresses ahead the crack tip. The T~ integral is employed as the crack extension criterion. This integral parameter accounts for the near tip stress-Strain Singularity and its critical values for crack propagation can be extracted from the P-Aa curve of single cracked specimen case. The present method can be applied to the problems of the fuselage skin of aging airplanes, in which a row of cracks develop (MSD; Multiple Site Damage) from rivet holes. The load carrying capacity of such damaged structure reduces by a considerable amount. In order to predict the behavior near the critical load, one must account for plastic deformation, if the material is ductile. Furthermore, the maximum load carried by the structure is often reached after some amount of crack propagation. In this paper, a series of analyses have been conducted and their results compare with the available experimental data.

  • Residual strength prediction for aircraft panels with Multiple Site Damage, using the “EPFEAM” for stable crack growth analysis
    Computational Mechanics, 1995
    Co-Authors: C. R. Pyo, Hiroshi Okada, Satya N Atluri
    Abstract:

    In this paper, a new analytical method for solving stable crack propagation problems in a ductile panel with a row of cracks, is presented. The main purpose of the present study is to estimate the maximum load carrying capacity of such panels accurately. The so called Elastic Plastic Finite Element Alternating Method (Pyo et al. (1994) was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stresses ahead the crack tip. The T infe sup* integral is employed as the crack extension criterion. This integral parameter accounts for the near tip stress-Strain Singularity and its critical values for crack propagation can be extracted from the P-Δa curve of single cracked specimen case. The present method can be applied to the problems of the fuselage skin of aging airplanes, in which a row of cracks develop (MSD; Multiple Site Damage) from rivet holes. The load carrying capacity of such damaged structure reduces by a considerable amount. In order to predict the behavior near the critical load, one must account for plastic deformation, if the material is ductile. Furthermore, the maximum load carried by the structure is often reached after some amount of crack propagation. In this paper, a series of analyses have been conducted and their results compare with the available experimental data.

C. R. Pyo - One of the best experts on this subject based on the ideXlab platform.

  • Residual strength prediction for aircraft panels with Multiple Site Damage, using the "EPFEAM" for stable crack growth analysis
    Computational Mechanics, 1995
    Co-Authors: C. R. Pyo, Hiroshi Okada, Satya N Atluri
    Abstract:

    190 Abstract In this paper, a new analytical method for solving stable crack propagation problems in a ductile panel with a row of cracks, is presented. The main purpose of the present study is to estimate the maximum load carrying capacity of such panels accurately. The so called Elastic Plastic Finite Element Alternating Method (Pyo et al. (1994)) was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stresses ahead the crack tip. The T~ integral is employed as the crack extension criterion. This integral parameter accounts for the near tip stress-Strain Singularity and its critical values for crack propagation can be extracted from the P-Aa curve of single cracked specimen case. The present method can be applied to the problems of the fuselage skin of aging airplanes, in which a row of cracks develop (MSD; Multiple Site Damage) from rivet holes. The load carrying capacity of such damaged structure reduces by a considerable amount. In order to predict the behavior near the critical load, one must account for plastic deformation, if the material is ductile. Furthermore, the maximum load carried by the structure is often reached after some amount of crack propagation. In this paper, a series of analyses have been conducted and their results compare with the available experimental data.

  • Residual strength prediction for aircraft panels with Multiple Site Damage, using the “EPFEAM” for stable crack growth analysis
    Computational Mechanics, 1995
    Co-Authors: C. R. Pyo, Hiroshi Okada, Satya N Atluri
    Abstract:

    In this paper, a new analytical method for solving stable crack propagation problems in a ductile panel with a row of cracks, is presented. The main purpose of the present study is to estimate the maximum load carrying capacity of such panels accurately. The so called Elastic Plastic Finite Element Alternating Method (Pyo et al. (1994) was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stresses ahead the crack tip. The T infe sup* integral is employed as the crack extension criterion. This integral parameter accounts for the near tip stress-Strain Singularity and its critical values for crack propagation can be extracted from the P-Δa curve of single cracked specimen case. The present method can be applied to the problems of the fuselage skin of aging airplanes, in which a row of cracks develop (MSD; Multiple Site Damage) from rivet holes. The load carrying capacity of such damaged structure reduces by a considerable amount. In order to predict the behavior near the critical load, one must account for plastic deformation, if the material is ductile. Furthermore, the maximum load carried by the structure is often reached after some amount of crack propagation. In this paper, a series of analyses have been conducted and their results compare with the available experimental data.

Hiroshi Okada - One of the best experts on this subject based on the ideXlab platform.

  • Residual strength prediction for aircraft panels with Multiple Site Damage, using the "EPFEAM" for stable crack growth analysis
    Computational Mechanics, 1995
    Co-Authors: C. R. Pyo, Hiroshi Okada, Satya N Atluri
    Abstract:

    190 Abstract In this paper, a new analytical method for solving stable crack propagation problems in a ductile panel with a row of cracks, is presented. The main purpose of the present study is to estimate the maximum load carrying capacity of such panels accurately. The so called Elastic Plastic Finite Element Alternating Method (Pyo et al. (1994)) was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stresses ahead the crack tip. The T~ integral is employed as the crack extension criterion. This integral parameter accounts for the near tip stress-Strain Singularity and its critical values for crack propagation can be extracted from the P-Aa curve of single cracked specimen case. The present method can be applied to the problems of the fuselage skin of aging airplanes, in which a row of cracks develop (MSD; Multiple Site Damage) from rivet holes. The load carrying capacity of such damaged structure reduces by a considerable amount. In order to predict the behavior near the critical load, one must account for plastic deformation, if the material is ductile. Furthermore, the maximum load carried by the structure is often reached after some amount of crack propagation. In this paper, a series of analyses have been conducted and their results compare with the available experimental data.

  • Residual strength prediction for aircraft panels with Multiple Site Damage, using the “EPFEAM” for stable crack growth analysis
    Computational Mechanics, 1995
    Co-Authors: C. R. Pyo, Hiroshi Okada, Satya N Atluri
    Abstract:

    In this paper, a new analytical method for solving stable crack propagation problems in a ductile panel with a row of cracks, is presented. The main purpose of the present study is to estimate the maximum load carrying capacity of such panels accurately. The so called Elastic Plastic Finite Element Alternating Method (Pyo et al. (1994) was extended to account for the propagating cracks. The crack propagation algorithm utilizes the analytic crack solution to release the stresses ahead the crack tip. The T infe sup* integral is employed as the crack extension criterion. This integral parameter accounts for the near tip stress-Strain Singularity and its critical values for crack propagation can be extracted from the P-Δa curve of single cracked specimen case. The present method can be applied to the problems of the fuselage skin of aging airplanes, in which a row of cracks develop (MSD; Multiple Site Damage) from rivet holes. The load carrying capacity of such damaged structure reduces by a considerable amount. In order to predict the behavior near the critical load, one must account for plastic deformation, if the material is ductile. Furthermore, the maximum load carried by the structure is often reached after some amount of crack propagation. In this paper, a series of analyses have been conducted and their results compare with the available experimental data.

Anil Kakodkar - One of the best experts on this subject based on the ideXlab platform.

  • Two end variable Singularity boundary elements and their applications in crack–crack interaction problems
    International Journal for Numerical Methods in Engineering, 2000
    Co-Authors: N. K. Mukhopadhyay, Surjya Kumar Maiti, Anil Kakodkar
    Abstract:

    SUMMARY Two new boundary elements have been proposed for simulation of variable order singularities at the two ends of an element in two dimensions. The "rst can model the variable order Strain Singularity at both the ends of the element. The second element can do both the Strain and traction singularities simultaneously. The elements are useful for studying the interaction of singularities as in the case of multiple neighbouring cracks in a domain. They are employed here for the computation of stress intensity factors (SIFs) in the crack}crack interaction problems. To improve the accuracy of such computations further a modi"ed crack closure integral (MCCI) based method for mechanical and/or thermal loading is presented. Examples of mode I crack and mixed mode problems under mechanical loading are studied to illustrate the performance of the proposed elements and the MCCI-based calculations. The e!ects of the order of Gauss quadrature associated with such elements on the accuracy of the SIFs are also reported. Copyright ( 2000 John Wiley & Sons, Ltd.

  • Variable Singularity boundary element and its applications in computation of SIFs
    Computers & Structures, 2000
    Co-Authors: N. K. Mukhopadhyay, Surjya Kumar Maiti, Anil Kakodkar
    Abstract:

    Two boundary elements have been proposed for simulation of variable order singularities in two dimensions. The first can model the variable order Strain Singularity near a crack tip and the second can simulate both the Strain and traction. These elements can be easily incorporated in a standard boundary element computer programme. The elements are useful for computation of stress intensity factors (SIFs) in fracture mechanics. To improve the accuracy of such computations further, a modified crack closure integral (MCCI) based method for mechanical loading are presented. Examples of mode I and mixed mode crack problems are examined to illustrate the performance of the proposed elements and the MCCI based calculations. The effects of order of Gauss quadrature associated with such elements on the accuracy of the SIFs are also reported.

Keh Chih Hwang - One of the best experts on this subject based on the ideXlab platform.

  • Dynamic asymptotic fields near a crack tip growing in a power-law hardening compressible material
    Mechanics of Materials, 1996
    Co-Authors: Keh Chih Hwang
    Abstract:

    Abstract Dynamic asymptotic stress and Strain fields near a mode I crack tip growing in a power-law hardening compressible material are studied under plane Strain conditions. By use of the J 2 flow theory and the rectangular components of field quantities, this paper obtains, through rigorous mathematical analysis, the asymptotic fields in which the stress- and Strain-Singularity are different, the angular variations of the fields are identical with those corresponding to dynamic crack in an elastic-perfectly plastic material. Finally, the results as the compressible material goes to be incompressible are discussed, and the numerical angular distributions of stress components are given.