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  • Chemistry  (40)
  • seismic processing/methodology  (4)
  • 72.40  (3)
  • STRUCTURAL MECHANICS  (3)
  • Spacecraft Design, Testing and Performance  (2)
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  • 1
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    In:  Geophysical Journal International 113: 225-238
    Publication Date: 1993
    Keywords: seismic processing/methodology
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  • 2
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    In:  Geophysical Journal International 110: 29-41
    Publication Date: 1992
    Keywords: seismic processing/methodology
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  • 3
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    In:  Geophysics 52: 1483-1491
    Publication Date: 1987
    Keywords: seismic processing/methodology
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  • 4
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    In:  Journal of Geophysics 60: 19-27
    Publication Date: 1986
    Keywords: seismic processing/methodology
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  • 5
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    In:  CASI
    Publication Date: 2016-06-07
    Description: Apollo project - progress and national benefits
    Keywords: STRUCTURAL MECHANICS
    Type: Proceedings of the Fourth National Conference on the Peaceful Uses of Space; NASA-SP-51
    Format: application/pdf
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  • 6
    Publication Date: 2019-06-27
    Description: Structural mechanics of deformation and fracture - responses of model viscoelastic materials to impact
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-80918
    Format: application/pdf
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  • 7
    Publication Date: 2019-07-12
    Description: The Laser Interferometer Space Antenna (LISA) is a mission designed to detect low frequency gravitational-waves. In order for LISA to succeed in its goal of direct measurement of gravitational waves, many subsystems must work together to measure the distance between proof masses on adjacent spacecraft. One such subsystem, the telescope, plays a critical role as it is the laser transmission and reception link between spacecraft. Not only must the material that makes up the telescope support structure be strong, stiff and light, but it must have a dimensional stability of better than 1 pm Hz(exp -1/2) at 3 mHz and the distance between the primary and the secondary mirrors must change by less than 2.5 micron over the mission lifetime. CFRP is the current baseline materiaL however, it has not been tested to the pico-meter level as required by the LISA mission. In this paper we present dimensional stability results, outgassing effects occurring in the cavity and discuss its feasibility for use as the telescope spacer for the LISA spacecraft.
    Keywords: Spacecraft Design, Testing and Performance
    Type: GSFC.JA.5667.2011
    Format: application/pdf
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  • 8
    Publication Date: 2019-06-27
    Description: Mechanical behavior of materials with temperature dependent viscosity, using electric analogy on nonlinear Maxwell model
    Keywords: STRUCTURAL MECHANICS
    Type: ; ACE(
    Format: text
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  • 9
    Publication Date: 2019-07-13
    Description: The LISA mission observes gravitational waves by measuring the separations between freely floating proof masses located 5 million kilometers apart with an accuracy of - 10 picometers. The separations are measured interferometrically. The telescope is an afocal Cassegrain style design with a magnification of 80x. The entrance pupil has a 40 cm diameter and will either be centered on-axis or de-centered off-axis to avoid obscurations. Its two main purposes are to transform the small diameter beam used on the optical bench to a diffraction limited collimated beam to efficiently transfer the metrology laser between spacecraft, and to receive the incoming light from the far spacecraft. It transmits and receives simultaneously. The basic optical design and requirements are well understood for a conventional telescope design for imaging applications, but the LISA design is complicated by the additional requirement that the total optical path through the telescope must remain stable at the picometer level over the measurement band during the mission to meet the measurement accuracy. We describe the mechanical requirements for the telescope and the preliminary work that has been done to understand the materials and mechanical issues associated with the design of a passive metering structure to support the telescope and to maintain the spacing between the primary and secondary mirrors in the LISA on-orbit environment. This includes the requirements flowdown from the science goals, thermal modeling of the spacecraft and telescope to determine the expected temperature distribution, layout options for the telescope including an on- and off-axis design. Plans for fabrication and testing will be outlined.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 8th International LISA Symposium; Jun 28, 2010 - Jul 02, 2010; Stanford, CA; United States
    Format: application/pdf
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  • 10
    Electronic Resource
    Electronic Resource
    Springer
    Applied physics 29 (1982), S. 63-68 
    ISSN: 1432-0630
    Keywords: 72.40 ; 73 ; 85 ; 60
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Notes: Abstract The electrical properties ofn +-window layers inp-i-n a-Si:H solar cells were characterised as a function ofn +-layer thickness, $$d_{n^ + } $$ , by measuring firstly the activation energyE a of the dark conductivity and secondly the built-in potentialV bi of the cells.E a was found to increase with decreasing $$d_{n^ + } $$ attaining values as high as 0.8 eV for $$d_{n^ + } $$ ≅5nm; bulk values, e.g.E a ≅. 2eV in the amorphous andE a〈0.01 eV in the microcrystalline case, were only observed for $$d_{n^ + } $$ 〉20nm and for $$d_{n^ + } $$ 〉200nm, respectively. In contrast,V bi did not depend on $$d_{n^ + } $$ at all and was further found to be consistent with expectations based on the Fermi level positions in bulkn + andp +-material. As a consequenceE a in very thin films can no longer be considered as a measure of (E C −E F), the distance of the Fermi level from the conduction band edge. The apparent inconsistency inherent to theE a and theV bi results can be resolved by assuming that the deposition of then +-material proceeds via the growth and coalescence of small islands.
    Type of Medium: Electronic Resource
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