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  • COMPOSITE MATERIALS  (5)
  • Humans
  • OCEANOGRAPHY
  • 2000-2004
  • 1990-1994  (2)
  • 1980-1984  (5)
  • 1994  (2)
  • 1984  (5)
  • 1
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    Unknown
    Mechanical property characterization and impact resistance of selected graphite/PEEK composite materials (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: To use graphite polyetheretherketone (PEEK) material on highly curved surfaces requires that the material be drapable and easily conformable to the surface. This paper presents the mechanical property characterization and impact resistance results for laminates made from two types of graphite/PEEK materials that will conform to a curved surface. These laminates were made from two different material forms. These forms are: (1) a fabric where each yarn is a co-mingled Celion G30-500 3K graphite fiber and PEEK thermoplastic fiber; and (2) an interleaved material of Celion G30-500 3K graphite fabric interleaved with PEEK thermoplastic film. The experimental results from the fabric laminates are compared with results for laminates made from AS4/PEEK unidirectional tape. The results indicate that the tension and compression moduli for quasi-isotropic and orthotropic laminates made from fabric materials are at least 79 percent of the modulus of equivalent laminates made from tape material. The strength of fabric material laminates is at least 80 percent of laminates made from tape material. The evaluation of fabric material for shear stiffness indicates that a tape material laminate could be replaced by a fabric material laminate and still maintain 89 percent of the shear stiffness of the tape material laminate. The notched quasi-isotropic compression panel failure strength is 42 to 46 percent of the unnotched quasi-isotropic laminate strength. Damage area after impact with 20 ft-lbs of impact energy is larger for the co-mingled panels than for the interleaved panels. The inerleaved panels have less damage than panels made from tape material. Residual compression strength of quasi-isotropic panels after impact of 20 ft-lbs of energy varies between 33 percent of the undamaged quasi-isotropic material strength for the tape material and 38 percent of the undamaged quasi-isotropic material strength for the co-mingled fabric material.
    Keywords: COMPOSITE MATERIALS
    Type: Journal of the American Helicopter Society (ISSN 0002-8711); 39; 1; p. 24-30
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Ground exposure of composite materials for helicopters (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Residual strength results are presented on four composite material systems that were exposed for three years at locations on the North American Continent. The exposure locations are near the areas where Bell Model 206L Helicopters, that are in a NSA/U.S. Army sponsored flight service program, are flying in daily commercial service. The composite systems are: (1) Kevlar-49 fabric/F-185 epoxy; (2) Kevlar-49 fabric/LRF-277 epoxy; (3) Kevlar-49 fabric/CE-306 epoxy; and (4) T-300 Graphite/E-788 epoxy. All material systems exhibited good strength retention in compression and short beam shear. The Kevlar-49/LRF-277 epoxy retained 88 to 93 percent of the baseline strength while the other material systems exceeded 95 percent of baseline strength. Residual tensile strength of all materials did not show a significant reduction. The available moisture absorption data is also presented.
    Keywords: COMPOSITE MATERIALS
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Rapid evolution of a Gulf Stream warm-core ring (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Satellite images are used to show that major alterations in the structure of Gulf Stream warm-core rings can occur during very short periods of two to five days when an interaction with the Gulf Stream is particularly intense. The role of these interactions in the evolution of a ring are discussed.
    Keywords: OCEANOGRAPHY
    Type: Nature (ISSN 0028-0836); 308; 837-840
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Worldwide flight and ground-based exposure of composite materials (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The long-term durability of those advanced composite materials which are applicable to aircraft structures was discussed. The composite components of various military and commercial aircraft and helicopters were reviewed. Both ground exposure and flight service were assessed in terms of their impact upon composite structure durability. The ACEE Program is mentioned briefly.
    Keywords: COMPOSITE MATERIALS
    Type: ACEE Composite Struct. Technol.; p 17-50
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    The analysis of ocean optical data (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new oceanographic instrument to measure underwater optical, biological and physical properties simultaneously has been built and used extensively at sea. The Bio-Optical Profiling System (BOPS) was designed for the rapid acquisition of data to accommodate shipboard 'synoptic' sampling strategies, often in conjunction with concurrent aircraft and satellite sensors. The data rates and associated quantity of data from the BOPS are some orders of magnitude larger than those traditionally encountered in optical oceanography. The rapid acquisition of optical data in a wide range of environmental conditions requires new methodologies in ocean optical data analysis.
    Keywords: OCEANOGRAPHY
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Ten-year ground exposure of composite materials used on the Bell Model 206L helicopter flight service program (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Residual strength results are presented for four composite material systems that have been exposed for up to 10 years to the environment at five different locations on the North American continent. The exposure locations are near where the Bell Model 206L helicopters, which participated in a flight service program sponsored by NASA Langley Research Center and the U.S. Army, were flying in daily commercial service. The composite material systems are (1) Kevlar-49 fabric/F-185 epoxy; (2) Kevlar-49 fabric/LRF-277 epoxy; (3) Kevlar-49 fabric/CE-306 epoxy; and (4) T-300 graphite/E-788 epoxy. Six replicates of each material were removed and tested after 1, 3, 5, 7, and 10 years of exposure. The average baseline strength was determined from testing six as-fabricated specimens. More than 1700 specimens have been tested. All specimens that were tested to determine their strength were painted with a polyurethane paint. Each set of specimens also included an unpainted panel for observing the weathering effects on the composite materials. A statistically based procedure has been used to determine the strength value above which at least 90 percent of the population is expected to fall with a 95-percent confidence level. The computed compression strengths are 80 to 90 percent of the baseline (no-exposure) strengths. The resulting compression strengths are approximately 8 percent below the population mean strengths. The computed short-beam-shear strengths are 83 to 92 percent of the baseline (no-exposure) strengths. The computed tension strength of all materials is 93 to 97 percent of the baseline (no-exposure) strengths.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-3468 , L-17341 , ARL-TR-480 , NAS 1.60:3468
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Ground exposure of composite materials for helicopters (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Residual strength results are presented on four composite material systems that were exposed for three years at locations on the North American Continent. The exposure locations are near the areas where Bell Model 206L Helicopters, that are in a NSA/U.S. Army sponsored flight service program, are flying in daily commercial service. The composite systems are: (1) Kevlar-49 fabric/F-185 epoxy; (2) Kevlar-49 fabric/LRF-277 epoxy; (3) Kevlar-49 fabric/CE-306 epoxy; and (4) T-300 Graphite/E-788 epoxy. All material systems exhibited good strength retention in compression and short beam shear. The Kevlar-49/LRF-277 epoxy retained 88 to 93 percent of the baseline strength while the other material systems exceeded 95 percent of baseline strength. Residual tensile strength of all materials did not show a significant reduction. The available moisture absorption data is also presented.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-86311 , AVSCOM-TM-84-B-2 , NAS 1.15:86311 , AHS Natl. Spec. Meeting-Helicopter Testing Technol.; Oct 29, 1984 - Nov 01, 1984; Williamsburg, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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