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  • 1
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    Technology integration box beam failure study (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of this paper is to describe current results from an on-going study of the mechanisms that led to the failure of the TIBB. Experimental and analytical results are presented. Experimental results include load, strain, and deflection data for the TIBB (Technology Integration Box Beam). An analytical investigation was conducted to compliment the experimental investigation and to gain additional insight into the TIBB structural response. Analytical results include strain and deflection results from a global analysis of the TIBB. A local analysis of the failure region is being completed. These analytical results are validated through comparisons with the experimental results from the TIBB tests. The experimental and analytical results from the TIBB tests are used to determine a sequence of events that may have resulted in failure of the TIBB. A potential cause of failure is high stresses in a stiffener runout region. Typical analytical results are presented for a stiffener runout specimen that is being defined to simulate the TIBB failure mechanisms. The results of this study are anticipated to provide better understanding of potential failure mechanisms in composite aircraft structures, to lead to future design improvements, and to identify needed analytical tools for design and analysis.
    Keywords: STRUCTURAL MECHANICS
    Type: FAA, Ninth DOD(NASA)FAA Conference on Fibrous Composites in Structural Design, Volume 2; p 673-68
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  • 2
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    Technology integration box beam failure study (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Composite structures have the potential to be cost-effective, structurally efficient primary aircraft structures. The Advanced Composites Technology (ACT) Program has the goal to develop the technology to exploit this potential for heavily loaded aircraft structures. As part of the ACT Program, Lockheed Aeronautical Systems Company completed the design and fabrication of the Technology Integration Box Beam (TIBB). The TIBB is an advanced composite prototype structure for the center wing section of the C-130 aircraft. Lockheed subjected the TIBB to downbending, upbending, torsion and combined upbending and torsion load conditions to verify the design. The TIBB failed at 83 percent of design ultimate load for the combined upbending and torsion load condition. The objective of this paper is to describe the mechanisms that led to the failure of the TIBB. The results of a comprehensive analytical and experimental study are presented. Analytical results include strain and deflection results from both a global analysis of the TIBB and a local analysis of the failure region. These analytical results are validated by experimental results from the TIBB tests. The analytical and experimental results from the TIBB tests are used to determine a sequence of events that resulted in failure of the TIBB. A potential cause of failure is high stresses in a stiffener runout region. Analytical and experimental results are also presented for a stiffener runout specimen that was used to simulate the TIBB failure mechanisms.
    Keywords: STRUCTURAL MECHANICS
    Type: Third NASA Advanced Composites Technology Conference, Volume 1, Part 2; p 951-965
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  • 3
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    Computation of strain energy release rates for skin-stiffener debonds modeled with plate elements (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An efficient method for predicting the strength of debonded composite skin-stiffener configurations is presented. This method, which is based on fracture mechanics, models the skin and the stiffener with two-dimensional (2D) plate elements instead of three-dimensional (3D) solid elements. The skin and stiffener flange nodes are tied together by two modeling techniques. In one technique, the corresponding flange and skin nodes are required to have identical translational and rotational degrees-of-freedom. In the other technique, the corresponding flange and skin nodes are only required to have identical translational degrees-of-freedom. Strain energy release rate formulas are proposed for both modeling techniques. These formulas are used for skin-stiffener debond cases with and without cylindrical bending deformations. The cylindrical bending results are compared with plane-strain finite element results. Excellent agreement between the two sets of results is obtained when the second technique is used. Thus, from these limited studies, a preferable modeling technique for skin-stiffener debond analysis using plate elements is established.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 93-1501 , In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 3 (A93-33876 1; p. 1680-1692.
    Format: text
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  • 4
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    The axisymmetric response of cylindrical and hemispherical shells to time-dependent loading (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Dynamic response of complete cylindrical shell obtained by thin shell bending theory
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-572
    Format: application/pdf
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  • 5
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    Dynamic Response of a Cylindrical Shell Segment Subjected to an Arbitrary Loading (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Dynamic response analysis for underground cylindrical shell segments subjected to blast loading
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-67184
    Format: application/pdf
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  • 6
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    Axisymmetric response of conical shells to blast load (1964)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Dynamic response of thin elastic conical shells subject to blast loading - membrane theory
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-58733
    Format: application/pdf
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  • 7
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    Skin-stiffener interface stresses in composite stiffened panels (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A model and solution method for determining the normal and shear stresses in the interface between the skin and the stiffener attached flange were developed. An efficient, analytical solution procedure was developed and incorporated in a sizing code for stiffened panels. The analysis procedure described provides a means to study the effects of material and geometric design parameters on the interface stresses. These stresses include the normal stress, and the shear stresses in both the longitudinal and the transverse directions. The tendency toward skin/stiffener separation may therefore be minimized by choosing appropriate values for the design variables. The most important design variables include the relative bending stiffnesses of the skin and stiffener attached flange, the bending stiffness of the stiffener web, and the flange width. The longitudinal compressive loads in the flange and skin have significant effects on the interface stresses.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-172261 , NAS 1.26:172261
    Format: application/pdf
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  • 8
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    Axisymmetric Dynamic Response of Spherical and Cylindrical Shells (1966)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Axisymmetric dynamic response of spherical and cylindrical shells
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-80370
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  • 9
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    The axisymmetric response of a complete cylindrical shell to shock loads. (1967)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Axisymmetric dynamic response of complete cylindrical shell to shock loads using bending theory of thin shells
    Keywords: STRUCTURAL MECHANICS
    Format: text
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  • 10
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    Liquid sloshing in elastic containers (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Coupled oscillations of elastic container partially filled with incompressible liquid
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-882
    Format: application/pdf
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