Propagation and control of crack-like damage in curved composite panels under combined loads

Mahler, Mary A.; Ley, Robert P.; Shah, Chandu; Lin, W.; Rouse, Marshall

doi:10.2514/6.2000-1534

Cited by 1 publication

(2 citation statements)

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“…A detailed description of the test panel is presented in Ref. 54. A photograph of the panel is shown in Fig.…”

Section: Combined Loads Test Hsr Fuselage Panelsmentioning

confidence: 99%

“…To prevent this undesirable deformation, cross bars are mounted between the hinge points as shown in the figure such that the distance between the hinge points can be held constant or adjusted as needed to induce the appropriate A curved sandwich fuselage panel with a centrally located circumferential sawcut through the facesheet and honeycomb core of the panel was subjected to internal pressure, shear and axial loading using the Dbox test fixture in the COLTS combined loads test machine (Ref. 54). The sandwich facesheets were fabriated from IM7/PETI-5 uni-directional tape with longitudinal tear straps, and the core is a titanium honeycomb core.…”

Section: Combined Loads Test Hsr Fuselage Panelsmentioning

confidence: 99%

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Utilization of the Building-Block Approach in Structural Mechanics Research

Rouse

Jegley

McGowan

et al. 2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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In the last 20 years NASA has worked in collaboration with industry to develop enabling technologies needed to make aircraft safer and more affordable, extend their lifetime, improve their reliability, better understand their behavior, and reduce their weight. To support these efforts, research programs starting with ideas and culminating in full-scale structural testing were conducted at the NASA Langley Research Center. Each program contained development efforts that (a) started with selecting the material system and manufacturing approach; (b) moved on to experimentation and analysis of small samples to characterize the system and quantify behavior in the presence of defects like damage and imperfections; (c) progressed on to examining larger structures to examine buckling behavior, combined loadings, and built-up structures; and (d) finally moved to complicated subcomponents and full-scale components. Each step along the way was supported by detailed analysis, including tool development, to prove that the behavior of these structures was well-understood and predictable. This approach for developing technology became known as the "building-block" approach. In the Advanced Composites Technology Program and the High Speed Research Program the building-block approach was used to develop a true understanding of the response of the structures involved through experimentation and analysis. The philosophy that if the structural response couldn't be accurately predicted, it wasn't really understood, was critical to the progression of these programs. To this end, analytical techniques including closed-form and finite elements were employed and experimentation used to verify assumptions at each step along the way. This paper presents a discussion of the utilization of the building-block approach described previously in structural mechanics research and development programs at NASA Langley Research Center. Specific examples that illustrate the use of this approach are included from recent research and development programs for both subsonic and supersonic transports.

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“…A detailed description of the test panel is presented in Ref. 54. A photograph of the panel is shown in Fig.…”

Section: Combined Loads Test Hsr Fuselage Panelsmentioning

confidence: 99%

Section: Combined Loads Test Hsr Fuselage Panelsmentioning

confidence: 99%