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  • 1
    facet.materialart.
    Unknown
    Stress concentration around a small circular hole in the HiMAT composite plate (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Anisotropic plate theory is used to calculate the anisotropic stress concentration factors for a composite plate (AS/3501-5 graphite/epoxy composite, single ply or laminated) containing a circular hole. This composite material is used on the highly maneuverable aircraft technology (HiMAT) vehicle. It is found that the anisotropic stress concentration factor could be greater or less than 3 (the stress concentration factor for isotropic materials), and that the locations of the maximum tangential stress points could shift with the change of fiber orientation with respect to the loading axis. The effect of hole size on the stress concentration factor is examined using the Point Stress Criterion and the Averaged Stress Criterion. The predicted stress concentration factors based on the two theories compared fairly well with the measured values for the hole size 0.3175 cm (1/8 in). It is also found that through the lamination process, the stress concentration factor could be reduced drastically, indicating an improvement in structural performance.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-86038 , H-1235 , NAS 1.15:86038
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Compression panel studies for supersonic cruise vehicles (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of analytical and experimental studies are summarized for titanium, boron fiber reinforced aluminum matrix composite, Borsic fiber reinforced aluminum matrix composite, and titanium sheathed Borsic fiber reinforced aluminum matrix composite stiffened panels. The results indicate that stiffened panels with continuous joints (i.e., brazed, diffusion bonded or adhesive bonded joints) are more structurally efficient than geometrically similar panels with discrete joints (i.e., spotwelded or bolted joints). In addition, results for various types of fiber reinforced aluminum matrix stiffened panels indicate that titanium sheathed Borsic fiber reinforced aluminum matrix composite panels are the most structurally efficient. Analytical results are also presented for graphite fiber reinforced polyimide matrix composite stiffened panels and superplastically formed and diffusion bonded titanium sandwich panels.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-1617 , L-13525 , NAS 1.60:1617
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Superplastically formed diffusion bonded metallic structure (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A metallic sandwich structure particularly suited for use in aerospace industries comprising a base plate, a cover plate, and an orthogonally corrugated core is described. A pair of core plates formed of a superplastic alloy are interposed between the base plate and the cover plate and bonded. Each of the core plates is characterized by a plurality of protrusions comprising square-based, truncated pyramids uniformly aligned along orthogonally related axes perpendicularly bisecting the legs of the bases of the pyramids and alternately inverted along orthogonally related planes diagonally bisecting the pyramids, whereby an orthogonally corrugated core is provided.
    Keywords: COMPOSITE MATERIALS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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