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  • Other Sources  (7)
  • 2010-2014  (4)
  • 1970-1974  (3)
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  • 1
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    Dipole and quadrupole integrals for the C I, N I, and O I sequences (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Coulomb approximation tables of Oertel and Shomo, together with binding-energy values obtained by a screening approximation, have been used to produce values of the dipole and quadrupole radial integrals needed in obtaining transition probabilities for ions of six, seven, and eight electrons. Some comparisons with more rigorously calculated values show that the present values are quite accurate, especially for ions of higher atomic number.
    Keywords: PHYSICS, ATOMIC, MOLECULAR, AND NUCLEAR
    Type: vol. 27; Mar. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Detection of radio emission from GX9+1. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Detection of a variable radio source in association with the X-ray source GX9+1, using the NRAO three-element interferometer at frequencies of 2695 and 8085 MHz. This radio source appears unresolved at all spacings, and must therefore be smaller than 1 arc sec. Two other celestial X-ray sources, GX349+2 and GX340+0 were also observed for radio emission during the same period of observations of GX9+1. These two sources should be good candidates for radio emission.
    Keywords: SPACE SCIENCES
    Type: Nature; 235; Feb. 18
    Format: text
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  • 3
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    Use of a New Portable Instrumented Impactor on the NASA Composite Crew Module Damage Tolerance Program (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Damage tolerance performance is critical to composite structures because surface impacts at relatively low energies may result in a significant strength loss. For certification, damage tolerance criteria require aerospace vehicles to meet design loads while containing damage at critical locations. Data from standard small coupon testing are difficult to apply to larger more complex structures. Due to the complexity of predicting both the impact damage and the residual properties, damage tolerance is demonstrated primarily by testing. A portable, spring-propelled, impact device was developed which allows the impact damage response to be investigated on large specimens, full-scale components, or entire vehicles. During impact, both the force history and projectile velocity are captured. The device was successfully used to demonstrate the damage tolerance performance of the NASA Composite Crew Module. The impactor was used to impact 18 different design features at impact energies up to 35 J. Detailed examples of these results are presented, showing impact force histories, damage inspection results, and response to loading.
    Keywords: Composite Materials
    Type: NF1676L-18063 , US-Japan Conference on Composite Materials; Sep 08, 2014 - Sep 10, 2014; La Jolla, CA; United States|ASTM-D30 Meeting; Sep 08, 2014 - Sep 10, 2014; La Jolla, CA; United States|American Society for Composites Technical Conference; Sep 08, 2014 - Sep 10, 2014; La Jolla, CA; United States
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  • 4
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    Structural Element Testing in Support of the Design of the NASA Composite Crew Module (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In January 2007, the NASA Administrator and Associate Administrator for the Exploration Systems Mission Directorate chartered the NASA Engineering and Safety Center (NESC) to design, build, and test a full-scale Composite Crew Module (CCM). For the design and manufacturing of the CCM, the team adopted the building block approach where design and manufacturing risks were mitigated through manufacturing trials and structural testing at various levels of complexity. Following NASA's Structural Design Verification Requirements, a further objective was the verification of design analysis methods and the provision of design data for critical structural features. Test articles increasing in complexity from basic material characterization coupons through structural feature elements and large structural components, to full-scale structures were evaluated. This paper discusses only four elements tests three of which include joints and one that includes a tapering honeycomb core detail. For each test series included are specimen details, instrumentation, test results, a brief analysis description, test analysis correlation and conclusions.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-13447 , SAMPE 2012; May 21, 2012 - May 24, 2012; Baltimore, MD; United States
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  • 5
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    Extended X-ray and radio observations of Scorpius X-1. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A 23-day observation reveals temporal variations at energies of 3-10 keV similar to those found in previous optical data. However, there is no evidence of more than one preferred intensity level or of an intensity threshold for flares. We rule out X-ray periodicities containing more than 5 per cent of the mean quiescent-period intensity with periods of from 6 minutes to 4 hours. The X-ray intensity is strongly correlated with hardness but is not correlated with radio data collected over eight days.
    Keywords: SPACE SCIENCES
    Type: Astrophysical Journal; 179; Jan. 1
    Format: text
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  • 6
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    A Model for Simulating the Response of Aluminum Honeycomb Structure to Transverse Loading (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A 1-dimensional material model was developed for simulating the transverse (thickness-direction) loading and unloading response of aluminum honeycomb structure. The model was implemented as a user-defined material subroutine (UMAT) in the commercial finite element analysis code, ABAQUS(Registered TradeMark)/Standard. The UMAT has been applied to analyses for simulating quasi-static indentation tests on aluminum honeycomb-based sandwich plates. Comparison of analysis results with data from these experiments shows overall good agreement. Specifically, analyses of quasi-static indentation tests yielded accurate global specimen responses. Predicted residual indentation was also in reasonable agreement with measured values. Overall, this simple model does not involve a significant computational burden, which makes it more tractable to simulate other damage mechanisms in the same analysis.
    Keywords: Composite Materials
    Type: NF1676L-14134 , 15th US-Japan Conference on Composite Materials Meeting; Oct 01, 2012 - Oct 03, 2012; Arlington, VA; United States|2012 American Society for Composites 27th Technical Conference; Oct 01, 2012 - Oct 03, 2012; Arlington, VA; United States
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  • 7
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    Investigation of the Leak Response of a Carbon-Fiber Laminate Loaded in Biaxial Tension (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Designers of pressurized structures have been reluctant to use composite materials because of concerns over leakage. Biaxial stress states are expected to be the worst-case loading condition for allowing leakage to occur through microcracks. To investigate the leakage behavior under in-plane biaxial loading, a cruciform composite specimen was designed that would have a relatively large test section with a uniform 1:1 biaxial loading ratio. A 7.6-cm-square test section was desired for future investigations of the leakage response as a result of impact damage. Many iterations of the cruciform specimen were evaluated using finite element analysis to reduce stress concentrations and maximize the size of the uniform biaxial strain field. The final design allowed the specimen to go to relatively high biaxial strain levels without incurring damage away from the test section. The specimen was designed and manufactured using carbon/epoxy fabric with a four-ply-thick, quasi-isotropic, central test section. Initial validation and testing were performed on a specimen without impact damage. The specimen was tested to maximum biaxial strains of approximately 4500micro epsilon without apparent damage. A leak measurement system containing a pressurized cavity was clamped to the test section and used to measure the flow rate through the specimen. The leakage behavior of the specimen was investigated for pressure differences up to 172 kPa
    Keywords: Composite Materials
    Type: NF1676L-16727 , American Society for Composites Annual Technical Conference; Sep 09, 2013 - Sep 11, 2013; State College, PA; United States
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