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  • 1
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    Evaluation and expansion of an analytical model for fatigue of notched composite laminates (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analytical and experimental study performed to expand the existing static and fatigue failure analysis is described. The analytical effort extended the analysis to include interlaminar effects, while the experimental effort developed methods to obtain basic experimental data required as input to the analysis. The static failure analysis for notched laminates was modified to include interlaminar effects near the notch. Three dimensional elastic and two dimensional elasticplastic finite element analysis were performed for some notched laminates.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-145308 , MSC/TFR/806/1025
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  • 2
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    Fatigue of notched fiber composite laminates. Part 1: Analytical model (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description is given of a semi-empirical, deterministic analysis for prediction and correlation of fatigue crack growth, residual strength, and fatigue lifetime for fiber composite laminates containing notches (holes). The failure model used for the analysis is based upon composite heterogeneous behavior and experimentally observed failure modes under both static and fatigue loading. The analysis is consistent with the wearout philosophy. Axial cracking and transverse cracking failure modes are treated together in the analysis. Cracking off-axis is handled by making a modification to the axial cracking analysis. The analysis predicts notched laminate failure from unidirectional material fatique properties using constant strain laminate analysis techniques. For multidirectional laminates, it is necessary to know lamina fatique behavior under axial normal stress, transverse normal stress and axial shear stress. Examples of the analysis method are given.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-132747 , MSC/TFR/7501
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  • 3
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    An investigation of the compressive strength of Kevlar 49/epoxy composites (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Tests were performed to evaluate the effect of a wide range of variables including matrix properties, interface properties, fiber prestressing, secondary reinforcement, and others on the ultimate compressive strength of Kevlar 49/epoxy composites. Scanning electron microscopy is used to assess the resulting failure surfaces. In addition, a theoretical study is conducted to determine the influence of fiber anisotropy and lack of perfect bond between fiber and matrix on the shear mode microbuckling. The experimental evaluation of the effect of various constituent and process characteristics on the behavior of these unidirectional composites in compression did not reveal any substantial increase in strength. However, theoretical evaluations indicate that the high degree of fiber anisotropy results in a significant drop in the predicted stress level for internal instability. Scanning electron microscope data analysis suggests that internal fiber failure and smooth surface debonding could be responsible for the measured low compressive strengths.
    Keywords: COMPOSITE MATERIALS
    Type: Composites; 6; Sept
    Format: text
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  • 4
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    Fatigue damage in notched composite laminates (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: This communication describes the results of an experimental investigation of the fatigue characteristics of a boron-epoxy laminate containing an unloaded circular hole. The study focuses upon characterization of the fatigue damage incurred and its influence upon axial tensile residual strength. Two apparent anomalies in the fatigue behavior for this laminate were observed. First, the fatigue damage was observed to propagate tangentially to the edge of the notch (parallel to the direction of the load), in contrast to propagation in contemporary metallic materials which is perpendicular to the load direction. Second, the residual strength characteristics for the laminate have revealed a significant increase in residual strength subsequent to a fatigue loading of 500,000 cycles at R = 0.1 and S = 0.8 and 0.67 (S = maximum stress/static ultimate). Failure analyses of the fatigue damage are conducted utilizing ultrasonic 'C' scan techniques.
    Keywords: COMPOSITE MATERIALS
    Type: Materials Science and Engineering; 30; Oct. 197
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  • 5
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    Fatigue of notched fiber composite laminates. Part 2: Analytical and experimental evaluation (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analytical/experimental correlation study was performed to develop an understanding of the behavior of notched Boron/epoxy laminates subjected to tension/tension fatigue loading. It is postulated that the fatigue induced property changes (stiffness as well as strength) of the laminate can be obtained from the lamina fatigue properties. To that end, the Boron/epoxy lamina static and fatigue data (lifetime, residual stiffness and strength) were obtained initially. The longitudinal and transverse tension data were determined from the (0) and (90) laminate tests while the in-plane shear data were obtained from the (+ or - 45) sub s laminates. The static tests obtained the notched strength and mode of failure while the fatigue tests determined lifetime, damage propagation and residual strength. The failure in static tension occurred in a transverse crack propagation mode.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-145039 , MSC/TFR/601/1025-PT-2
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  • 6
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    Fatigue of notched fiber composite laminates - Analytical and experimental evaluation (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Axial cracking in the load direction and transverse cracking across notched boron/epoxy laminate specimens subjected to tension/tension fatigue loading are studied both theoretically and experimentally. The fatigue analysis, which allows for the computation of residual strength and the determination of the preferred mode of crack propagation, is reviewed; static and fatigue data for boron/epoxy lamina are investigated with the aim of characterizing fatigue growth and residual strength as a function of the number of load cycles. It is suggested that correlation between the theory and the experiment may be limited by lack of a capability to predict the growth of delaminations.
    Keywords: COMPOSITE MATERIALS
    Type: Conference on Composite materials: Testing and design; May 03, 1976 - May 04, 1976; Valley Forge, PA
    Format: text
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  • 7
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    Failure and fatigue mechanisms in composite materials (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A phenomenological description of microfailure under monotonic and cyclic loading is presented, emphasizing the significance of material inhomogeneity for the analysis. Failure in unnotched unidirectional laminates is reviewed for the cases of tension, compression, shear, transverse normal, and combined loads. The failure of notched composite laminates is then studied, with particular attention paid to the effect of material heterogeneity on load concentration factors in circular holes in such laminates, and a 'materials engineering' shear-lay type model is presented. The fatigue of notched composites is discussed with the application of 'mechanistic wearout' model for determining crack propagation as a function of the number of fatigue cycles.-
    Keywords: COMPOSITE MATERIALS
    Type: Inelastic behavior of composite materials; Nov 30, 1975 - Dec 05, 1975; Houston, TX
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  • 8
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    An engineering approach to the prediction of fatigue behavior of unnotched/notched fiber reinforced composite laminates (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An engineering approach is proposed for predicting unnotched/notched laminate fatigue behavior from basic lamina fatigue data. The fatigue analysis procedure was used to determine the laminate property (strength/stiffness) degradation as a function of fatigue cycles in uniaxial tension and in plane shear. These properties were then introduced into the failure model for a notched laminate to obtain damage growth, residual strength, and failure mode. The approach is thus essentially a combination of the cumulative damage accumulation (akin to the Miner-Palmgren hypothesis and its derivatives) and the damage growth rate (similar to the fracture mechanics approach) philosophies. An analysis/experiment correlation appears to confirm the basic postulates of material wearout and the predictability of laminate fatigue properties from lamina fatigue data.
    Keywords: COMPOSITE MATERIALS
    Type: Reinforced Plastics/Composites Institute, Annual Conference; Feb 07, 1978 - Feb 10, 1978; Washington, DC
    Format: text
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