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  • Other Sources  (2)
  • 1985-1989  (2)
  • 1986  (2)
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  • 1985-1989  (2)
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  • 1
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    Unknown
    Space Shuttle Main Engine fuel preburner augmented spark igniter shutdown detonations (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Detonations were experienced in the Space Shuttle Main Engine fuel preburner (FPB) augmented spark igniter (ASI) during engine cutoff. Several of these resulted in over pressures sufficient to damage the FPB ASI oxidizer system. The detonations initiated in the FPB ASI oxidizer line when residual oxidizer (oxygen) in the line mixed with backflowing fuel (hydrogen) and detonated. This paper reviews the damage history to the FPB ASI oxidizer system, an engineering assessment of the problem cause, a verification of the mechanisms, the hazards associated with the detonations, and the solution implemented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 86-1445
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Impact resistance and interlaminar fracture toughness of through-the-thickness reinforced graphite/epoxy (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Five through-the-thickness stitch configurations are analyzed to determine the effect of impact resistance and interlaminar fracture toughness on T3000/3501-6 graphite/epoxy. The test specimens were stitched with either polyester or Kevlar yarns and with various stitch parameters. Tension and compression mechanical, impact and compression-after-impact, and double cantilever beam tests were conducted. It is observed that the stitched laminates have tension and compression strengths 20-25 percent lower than the strengths of unstitched laminates, the tension strength of stitched laminates is reduced with increasing number of stitches, and the compression strength increases as the number of stitches are increased. The impact data reveal that the Kevlar stitched laminates have less damage than unstitched laminates; the most effective configuration for suppressing impact damage and improving interlaminar fracture toughness consists of Kevlar yarns 1/4 inch apart with eight stitches per inch. The mode 1 critical strain energy release rate for the 1/4 inch Kevlar eight stitch laminate was calculated as 30 times higher than that of the unstitched.
    Keywords: COMPOSITE MATERIALS
    Type: AIAA PAPER 86-1020
    Format: text
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    NASA TECHNICAL REPORTS
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