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  • 1
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    In:  Int. J. for Num. and Analyt. Methods in Geomech., Amsterdam, Schweizerbart'sche Verlagsbuchhandlung, vol. 4, no. 12, pp. 25-43, pp. L12S09, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Publication Date: 1980
    Keywords: Fracture ; Rock mechanics ; Finite Element Method ; BO, ; RUB, ; Bauing. ; FROTH
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  • 2
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    The American Society of Mechanical Engineers
    In:  Professional Paper, Advanced Topics in Boundary Element Analysis, New York, The American Society of Mechanical Engineers, vol. 23, no. Subvol. b, pp. 205-211, (ISBN: 3-540-23712-7)
    Publication Date: 1985
    Keywords: Three dimensional ; Boundary Element Method ; Fracture
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  • 3
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    Academic Press
    In:  Bull., Polar Proj. OP-O3A4, Fracture Mechanics of Rock, London, Academic Press, vol. 560, no. XVI:, pp. 71-110, (ISBN: 3-540-23712-7)
    Publication Date: 1987
    Keywords: Fracture ; Rock mechanics ; Stress
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  • 4
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    The American Society of Mechanical Engineers
    In:  Professional Paper, Open-File Rept., Analytical, Numerical, and Experimental Aspects of Three Dimensional Fracture Processes, New York, The American Society of Mechanical Engineers, vol. 65, no. 16, pp. 321-327, (ISBN 0080419208)
    Publication Date: 1988
    Keywords: Fracture ; Three dimensional ; software
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  • 5
    Publication Date: 2009-11-16
    Description: The subject of this paper is the buckling of laminated plates, with a preexisting delamination, subjected to in-plane loading. Each laminate is modelled as an orthotropic Mindlin plate. The analysis is carried out by a combination of the finite element and asymptotic expansion methods. By applying the finite element method, plates with general delamination regions can be studied. The asymptotic expansion method reduces the number of unknown variables of the eigenvalue equation to that of the equation for a single Kirchhoff plate. Numerical results are presented for several examples. The effects of the shape, size, and position of the delamination on the buckling load are studied through these examples.
    Keywords: COMPOSITE MATERIALS
    Type: NASA. Langley Research Center, The Third Air Force(NASA Symposium on Recent Advances in Multidisciplinary Analysis and Optimization; p 482-487
    Format: text
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  • 6
    Publication Date: 2006-04-09
    Description: The establishment of the boundary element method (BEM) as a valid tool for solving problems in structural mechanics and in other fields of applied physics is discussed. The development of an integrated interactive computer graphic system for the application of the BEM to three dimensional problems in elastostatics is described. The integration of interactive computer graphic techniques and the BEM takes place at the preprocessing and postprocessing stages of the analysis process, when, respectively, the data base is generated and the results are interpreted. The interactive computer graphic modeling techniques used for generating and discretizing the boundary surfaces of a solid domain are outlined.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA. Langley Research Center Computer-Aided Geometry Modeling; p 215-222
    Format: text
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  • 7
    Publication Date: 2011-08-19
    Description: The general capabilities and the hardware environment of an interactive color graphical postprocessor for three-dimensional numerical analysis are described as well as the synergistic influence of this aspect of interactive graphics on the research environment. Areas of practical concern include finite element analysis, fracture propagation, surface and framed structures. The interactive color graphical postprocessor, POSTPRO3D, is capable of displaying the scalar, vector, and tensor results of finite difference, finite element, and boundary element analysis. In the case of fatigue cracking in steel crane-rail girders, it was shown that POSTPRO3D offers a high level of flexibility, interactivity and features which minimize response time.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: Finite Elements in Analysis and Design (ISSN 0168-874X); 2; 1-17
    Format: text
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  • 8
    Publication Date: 2019-06-28
    Description: FRANC 2D (FRacture ANalysis Code, 2 Dimensions) is a menu driven, interactive finite element computer code that performs fracture mechanics analyses of 2-D structures. The code has an automatic mesh generator for triangular and quadrilateral elements. FRANC2D calculates the stress intensity factor using linear elastic fracture mechanics and evaluates crack extension using several methods that may be selected by the user. The code features a mesh refinement and adaptive mesh generation capability that is automatically developed according to the predicted crack extension direction and length. The code also has unique features that permit the analysis of layered structure with load transfer through simulated mechanical fasteners or bonded joints. The code was written for UNIX workstations with X-windows graphics and may be executed on the following computers: DEC DecStation 3000 and 5000 series, IBM RS/6000 series, Hewlitt-Packard 9000/700 series, SUN Sparc stations, and most Silicon Graphics models.
    Keywords: METALLIC MATERIALS
    Type: NASA-CR-4572 , NAS 1.26:4572
    Format: application/pdf
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  • 9
    Publication Date: 2019-06-28
    Description: A methodology for simulating the growth of long through cracks in the skin of pressurized aircraft fuselage structures is described. Crack trajectories are allowed to be arbitrary and are computed as part of the simulation. The interaction between the mechanical loads acting on the superstructure and the local structural response near the crack tips is accounted for by employing a hierarchical modeling strategy. The structural response for each cracked configuration is obtained using a geometrically nonlinear shell finite element analysis procedure. Four stress intensity factors, two for membrane behavior and two for bending using Kirchhoff plate theory, are computed using an extension of the modified crack closure integral method. Crack trajectories are determined by applying the maximum tangential stress criterion. Crack growth results in localized mesh deletion, and the deletion regions are remeshed automatically using a newly developed all-quadrilateral meshing algorithm. The effectiveness of the methodology and its applicability to performing practical analyses of realistic structures is demonstrated by simulating curvilinear crack growth in a fuselage panel that is representative of a typical narrow-body aircraft. The predicted crack trajectory and fatigue life compare well with measurements of these same quantities from a full-scale pressurized panel test.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center, FAA(NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, Part 2; p 581-601
    Format: application/pdf
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  • 10
    Publication Date: 2019-06-28
    Description: In one scenario of a crack in an airplane fuselage, the crack is subjected to cyclic tensile and out of plane shearing loads. To predict the fatigue crack growth in such a situation, experiments are being performed to measure the crack growth rate in laboratory specimens subjected to similar loadings. The mechanics of this problem are reviewed, the energy release rate is calculated and designs for an experiment are discussed along with some preliminary experimental observations.
    Keywords: STRUCTURAL MECHANICS
    Type: In: International Congress on Experimental Mechanics, 7th, Las Vegas, NV, June 8-11, 1992, Proceedings. Vol. 1 (A94-12901 02-39); p. 44-50.
    Format: text
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