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  • Other Sources  (2)
  • Composite Materials; Aircraft Design, Testing and Performance  (1)
  • Spacecraft Design, Testing and Performance; Composite Materials; Structural Mechanics  (1)
  • Carbonate chemistry
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  • 1
    facet.materialart.
    Unknown
    An Analysis Methodology to Predict Damage Propagation in Notched Composite Fuselage Structures (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A new methodology is proposed for predicting damage propagation in notched composite skin-stiffened structures. The proposed approach considers the interaction of damage propagation in the skin with delamination of the stiffener in order to assess the damage containment behavior of the structure. The damage propagating from a notch within a thin fiber-reinforced polymer skin is idealized as a through-the-thickness cohesive crack. The cohesive law for the through-the-thickness crack is characterized using a compact tension test. The approach was applied to a full-scale pultruded rod stitched efficient unitized structure (PRSEUS) concept fuselage panel that was tested recently. The stitched skin/stringer interfaces, a key feature of the PRSEUS concept, were modeled to assess the effectiveness of the stitching at containing damage propagation. Comparison between the predicted and observed damage extension shows acceptable agreement throughout loading. These results indicate that the model can represent accurately the complex interactions between a through-the-thickness crack in the skin and delamination between the skin and stringer. The model is used to demonstrate that the skin-stiffener interface toughness is critical to damage containment capability
    Keywords: Composite Materials; Aircraft Design, Testing and Performance
    Type: NF1676L-21508 , Society for the Advancement of Material and Process Engineering Conference and Exhibition (SAMPE 2015); May 18, 2015 - May 21, 2015; Baltimore, MD; United States
    Format: application/pdf
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  • 2
    facet.materialart.
    Unknown
    A Numerical Study on the Edgewise Compression Strength of Sandwich Structures with Facesheet-Core Disbonds (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Damage tolerant design approaches require determination of critical damage modes and flaw sizes in order to establish nondestructive evaluation detection requirements. A finite element model is developed to assess the effect of circular facesheet-core disbonds on the strength of sandwich specimens subjected to edgewise compressive loads for the purpose of predicting the critical flaw size for a variety of design parameters. Postbuckling analyses are conducted in which an initial imperfection is seeded using results from a linear buckling analysis. Both the virtual crack closure technique (VCCT) and cohesive elements are considered for modeling disbond growth. Predictions from analyses using the VCCT and analyses using cohesive elements are in good correlation. A series of parametric analyses are conducted to investigate the effect of core thickness and material, facesheet layup, facesheet-core interface properties, and curvature on the criticality of facesheet-core disbonds of various sizes. The results from these analyses provide a basis for determining the critical flaw size for facesheet-core disbonds subjected to edgewise compression loads and, therefore, nondestructive evaluation flaw detection requirements for this configuration.
    Keywords: Spacecraft Design, Testing and Performance; Composite Materials; Structural Mechanics
    Type: NF1676L-24620 , AIAA SciTech 2017; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
    Format: application/pdf
    Location Call Number Expected Availability
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