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  • 1
    facet.materialart.
    Unknown
    The NASA structures and materials research program for supersonic cruise aircraft (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The structures and materials part of the NASA Supersonic Cruise Aircraft Research (SCAR) program is reviewed. It is pointed out that in more than three years of work significant new technology has been generated. The aircraft configurations which are efficient aerodynamically have aeroelastic problems that must be alleviated by configuration changes, active controls, or additional structural mass. An approach involving the application of advanced composite materials has the highest potential for structural weight reduction. Attention is given to the structural concepts for an arrow-wing supersonic aircraft and the techniques used in the investigations. It is expected that continuing research in SCAR structures and materials should bring high payoffs in the late 1980s.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 14; May 1976
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    NASA research on structures and materials for supersonic cruise aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The technology and data base necessary for sound technical decisions regarding long haul supersonic cruise aircraft transportation systems are considered. The objectives and status of the research elements in the structures and materials program phase of the program are reviewed. Emphasis is placed on reductions in structural mass by research on advanced structural concepts, light-weight materials, improved loads, aeroelastic predictive techniques, and by development of efficient structural design procedures.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-X-72790
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Elevated-temperature application of the IITRI compression test fixture for graphite/polyimide filamentary composites (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Seventy-nine graphite/polyimide compression specimens were tested to investigate experimentally the IITRI test method for determining compressive properties of composite materials at room and elevated temperatures (589 K (600 F)). Minor modifications were made to the standard IITRI fixture and a high degree of precision was maintained in specimen fabrication and load alignment. Specimens included four symmetric laminate orientations. Various widths were tested to evaluate the effect of width on measured modulus and strength. In most cases three specimens of each width were tested at room and elevated temperature and a polynomial regression analysis was used to reduce the data. Scatter of replicate tests and back-to-back strain variations were low, and no specimens failed by instability. Variation of specimen width had a negligible effect on the measured ultimate strengths and initial moduli of the specimens. Measured compressive strength and stiffness values were sufficiently high for the material to be considered a usable structural material at temperatures as high as 589 K (600 F).
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-1496 , L-12704
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A critical examination of stresses in an elastic single lap joint (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an approximate nonlinear finite-element analysis of a single lap joint are presented and compared with the results of a linear finite-element analysis, and the geometric nonlinear effects caused by the load-path eccentricity on the adhesive stress distributions are determined. The results from finite-element, Goland-Reissner, and photoelastic analyses show that for a single lap joint the effect of the geometric nonlinear behavior of the joint has a sizable effect on the stresses in the adhesive. The Goland-Reissner analysis is sufficiently accurate in the prediction of stresses along the midsurface of the adhesive bond to be used for qualitative evaluation of the influence of geometric or material parametric variations. Detailed stress distributions in both the adherend and adhesive obtained from the finite-element analysis are presented to provide a basis for comparison with other solution techniques.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-1507 , L-12802
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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