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  • 1
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    Comparison of impact results for several polymeric composites over a wide range of low impact velocities (1991)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: Static indentation, falling weight, and ballistic impact tests were conducted in clamped plates made of AS4/3501-6 and IM7/8551-7 prepreg tape. The transversely isotropic plates were nominally 7-mm thick. Pendulum and ballistic tests were also conducted on simply supported plates braided with Celion 12000 fibers and 3501-6 epoxy. The 20 degree braided plates were about 5-mm thick. The impactors had spherical or hemispherical shapes with a 12.7 mm diameter. Residual compression strength and damage size were measured. For a given kinetic energy, damage size was least for IM7/8551-7 and greatest for the braided material. Strengths varied inversely with damage size. For a given damage size, strength loss as a fraction of original strength was least for the braided material and greatest for AS4/3501-6 and IM7/8551-7. Strength loss for IM7/8551-7 and AS4/3501-6 was nearly equal. No significant differences were noticed between damage sizes and residual compression strengths for the static indentation, falling weight, and ballistic tests of AS4/3501-6 and IM7/8551-7. For the braided material, sizes of damage were significantly less and compression strengths were significantly more for the falling weight tests than for the ballistic tests.
    Schlagwort(e): COMPOSITE MATERIALS
    Materialart: First NASA Advanced Composites Technology Conference, Part 2; p 513-547
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Standard methods for open hole tension testing of textile composites (1995)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Sizing effects have been investigated by comparing the open hole failure strengths of each of the four different braided architectures as a function of specimen thickness, hole diameter, and the ratio of specimen width to hole diameter. The data used to make these comparisons was primarily generated by Boeing. Direct comparisons of Boeing's results were made with experiments conducted at West Virginia University whenever possible. Indirect comparisons were made with test results for other 2-D braids and 3-D weaves tested by Boeing and Lockheed. In general, failure strength was found to decrease with increasing plate thickness, increase with decreasing hole size, and decreasing with decreasing width to diameter ratio. The interpretation of the sensitive to each of these geometrical parameters was complicated by scatter in the test data. For open hole tension testing of textile composites, the use of standard testing practices employed by industry, such as ASTM D5766 - Standard Test Method for Open Hole Tensile Strength of Polymer Matrix Composite Laminates should provide adequate results for material comparisons studies.
    Schlagwort(e): COMPOSITE MATERIALS
    Materialart: NASA-CR-198262 , NAS 1.26:198262 , NIPS-96-08493
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    Standard Methods for Bolt-Bearing Testing of Textile Composites (1995)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The response of three 2-D braided materials to bolt bearing loading was evaluated using data generated by Boeing Defense and Space Group in Philadelphia, PA. Three test methods, stabilized single shear, unstabilized single shear, and double shear, were compared. In general, these textile composites were found to be sensitive to bolt bearing test methods. The stabilized single shear method yielded higher strengths than the unstabilized single shear method in all cases. The double shear test method always produced the highest strengths but these results may be somewhat misleading. It is therefore recommended that standard material comparisons be made using the stabilized single shear test method. The effects of two geometric parameters, W/D and e/D, were also studied. An evaluation of the effect of the specimen width (W) to hole diameter (D) ratio concluded that bolt bearing responses were consistent with open hole tension results. A W/D ratio of 6 or greater should be maintained. The proximity of the hole to the specimen edge significantly affected strength. In all cases, strength was improved by increasing the ratio of the distance from the hole center to the specimen edge (e) to the hole diameter (D) above 2. An e/D ratio of 3 or greater is recommended.
    Schlagwort(e): Composite Materials
    Materialart: NASA-CR-198266 , NAS 1.26:198266
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 4
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    Standard methods for filled hole tension testing of textile composites (1995)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The effects of two test specimen geometry parameters, the specimen width and W/D ratio, on filled-hole tensile strength were determined for textile composite materials. Test data generated by Boeing and Lockheed on 2-D and 3-D braids, and 3-D weaves were used to make these evaluations. The investigation indicated that filled-hole tensile-strength showed little sensitivity to either parameter. Test specimen configurations used in open-hole tension tests, such as those suggested by ASTM D5766 - Standard Test Method for Open Hole Tensile Strength of Polymer Matrix Composite Laminates or those proposed by MIL-HDBK-17-lD should provide adequate results for material comparisons studies. Comparisons of the materials' open-hole and filled-hole tensile strengths indicated that the latter were generally lower than the former. The 3-D braids were the exception; their filled-hole strengths were unexpected larger than their open-hole strengths. However, these increases were small compared to the scatter in the data. Thus, filled hole tension may be a critical design consideration for textile composite materials.
    Schlagwort(e): Composite Materials
    Materialart: NASA-CR-198263 , NAS 1.26:198263
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 5
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    Investigation of the flaw growth characteristics of 6Al-4V titanium used in the Apollo spacecraft pressure vessels (1967)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Failure analysis of flaw growth characteristics of 6Al-4V titanium forgings used in Apollo spacecraft propellant tanks
    Schlagwort(e): MATERIALS, METALLIC
    Materialart: NASA-CR-65586
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A study of weldments and pressure vessels made of HY-150 steel plates Final report, 8 Nov. 1965 - 9 Dec. 1966 (1967)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Gas tungsten arc method for optimal weldments in steel plates for large rocket motor case
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: NASA-CR-72155 , D2-113433-1
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Investigation of crack growth threshold of Inconel 718 exposed to high pressure oxygen Final report 24 Apr. - 25 May 1970 (1970)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Crack growth threshold investigation of Inconel 718 exposed to high pressure oxygen
    Schlagwort(e): MATERIALS, METALLIC
    Materialart: NASA-CR-108485
    Format: application/pdf
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  • 8
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    Fracture characteristics of structural aerospace alloys containing deep surface flaws (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Conditions controlling the growth and fracture of deep surface flaws in aerospace alloys were investigated. Static fracture tests were performed on 7075-T651 and 2219-T87 aluminum, and 6Ai-4V STA titanium . Cyclic flaw growth tests were performed on the two latter alloys, and sustain load tests were performed on the titanium alloy. Both the cyclic and the sustain load tests were performed with and without a prior proof overload cycle to investigate possible growth retardation effects. Variables included in all test series were thickness, flaw depth-to-thickness ratio, and flaw shape. Results were analyzed and compared with previously developed data to determine the limits of applicability of available modified linear elastic fracture solutions.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: NASA-CR-134587 , D180-17759-1
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 9
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    Flaw Growth of 6Al-4V Titanium in a Freon TF Environment (1969)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The plane strain threshold stress intensity and sustained stress flaw growth rates were experimentally determined for 6AI-4V S.T.A. titanium forging and weldments in environments of Freon TF at room temperature. Sustained load tests of surface flawed specimens were conducted with the experimental approach based on linear elastic fracture mechanics. It was concluded that sustained stress flaw growth rates, in conjunction with threshold stress intensities, can be used in assessing the service life of pressure vessels.
    Schlagwort(e): Structural Mechanics
    Materialart: NASA-CR-99632
    Format: application/pdf
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  • 10
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    A study of low-cost weldments in pressure vessels made up of HY-150 steel plates Final report, 6 Jun. 1967 - 31 Oct. 1968 (1968)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Low cost automated and manual welding techniques for pressure vessels made of HY-150 steel plates
    Schlagwort(e): MATERIALS, METALLIC
    Materialart: NASA-CR-72468 , D2-114408-1
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
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