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  • 1985-1989  (3)
  • 1985  (3)
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  • 1985-1989  (3)
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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
    facet.materialart.
    Unknown
    Impacts of Space Shuttle thermal protection system tile on F-15 aircraft vertical tile (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Impacts of the space shuttle thermal protection system (TPS) tile on the leading edge and the side of the vertical tail of the F-15 aircraft were analyzed under different TPS tile orientations. The TPS tile-breaking tests were conducted to simulate the TPS tile impacts. It was found that the predicted tile impact forces compare fairly well with the tile-breaking forces, and the impact forces exerted on the F-15 aircraft vertical tail were relatively low because a very small fraction of the tile kinetic energy was dissipated in the impact, penetration, and fracture of the tile. It was also found that the oblique impact of the tile on the side of the F-15 aircraft vertical tail was unlikely to dent the tail surface.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-85904 , H-1248 , NAS 1.15:85904
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Stress analyses of B-52 pylon hooks (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The NASTRAN finite element computer program was used in the two dimensional stress analysis of B-52 carrier aircraft pylon hooks: (1) old rear hook (which failed), (2) new rear hook (improved geometry), (3) new DAST rear hook (derated geometry), and (4) front hook. NASTRAN model meshes were generated by the aid of PATRAN-G computer program. Brittle limit loads for all the four hooks were established. The critical stress level calculated from NASTRAN agrees reasonably well with the values predicted from the fracture mechanics for the failed old rear hook.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-84924 , H-1221 , NAS 1.15:84924
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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