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  • 1
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    Part 6 - Lunar temperatures and thermal characteristics (1967)
    In:  CASI
    Details
    Publication Date: 2005-11-13
    Keywords: unknown
    Type: SURVEYOR 3 PRELIMINARY SCI. RESULTS 15 MAY 1967 (SEE N69-78676)
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Lunar temperatures and thermal characteristics (1967)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Surveyor III measurements of lunar surface temperatures and thermal characteristics
    Keywords: SPACE SCIENCES
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  • 3
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    Lunar temperatures and thermal characteristics (1967)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Surveyor III data on lunar surface temperatures, thermophysical characteristics, and spacecraft thermal performance on lunar surface
    Keywords: SPACE SCIENCES
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  • 4
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    Surveyor 3 results - Lunar temperatures and thermal characteristics. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Lunar surface temperatures and thermophysical characteristics measured by Surveyor 3, noting directional effects
    Keywords: SPACE SCIENCES
    Type: ; ADEMIE DES SCIENCES
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  • 5
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    Technology integration box beam failure study (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of this paper is to describe current results from an on-going study of the mechanisms that led to the failure of the TIBB. Experimental and analytical results are presented. Experimental results include load, strain, and deflection data for the TIBB (Technology Integration Box Beam). An analytical investigation was conducted to compliment the experimental investigation and to gain additional insight into the TIBB structural response. Analytical results include strain and deflection results from a global analysis of the TIBB. A local analysis of the failure region is being completed. These analytical results are validated through comparisons with the experimental results from the TIBB tests. The experimental and analytical results from the TIBB tests are used to determine a sequence of events that may have resulted in failure of the TIBB. A potential cause of failure is high stresses in a stiffener runout region. Typical analytical results are presented for a stiffener runout specimen that is being defined to simulate the TIBB failure mechanisms. The results of this study are anticipated to provide better understanding of potential failure mechanisms in composite aircraft structures, to lead to future design improvements, and to identify needed analytical tools for design and analysis.
    Keywords: STRUCTURAL MECHANICS
    Type: FAA, Ninth DOD(NASA)FAA Conference on Fibrous Composites in Structural Design, Volume 2; p 673-68
    Format: application/pdf
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  • 6
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    Technology integration box beam failure study (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Composite structures have the potential to be cost-effective, structurally efficient primary aircraft structures. The Advanced Composites Technology (ACT) Program has the goal to develop the technology to exploit this potential for heavily loaded aircraft structures. As part of the ACT Program, Lockheed Aeronautical Systems Company completed the design and fabrication of the Technology Integration Box Beam (TIBB). The TIBB is an advanced composite prototype structure for the center wing section of the C-130 aircraft. Lockheed subjected the TIBB to downbending, upbending, torsion and combined upbending and torsion load conditions to verify the design. The TIBB failed at 83 percent of design ultimate load for the combined upbending and torsion load condition. The objective of this paper is to describe the mechanisms that led to the failure of the TIBB. The results of a comprehensive analytical and experimental study are presented. Analytical results include strain and deflection results from both a global analysis of the TIBB and a local analysis of the failure region. These analytical results are validated by experimental results from the TIBB tests. The analytical and experimental results from the TIBB tests are used to determine a sequence of events that resulted in failure of the TIBB. A potential cause of failure is high stresses in a stiffener runout region. Analytical and experimental results are also presented for a stiffener runout specimen that was used to simulate the TIBB failure mechanisms.
    Keywords: STRUCTURAL MECHANICS
    Type: Third NASA Advanced Composites Technology Conference, Volume 1, Part 2; p 951-965
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  • 7
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    Technology integration box beam failure study (1992)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: Composite structures have the potential to be cost effective, structurally efficient primary aircraft structures. As part of the Advanced Composite Technology (ACT) program to exploit this potential for heavily loaded aircraft structures, the design and fabrication of the technology integration box beam (TIBB) was completed. The TIBB is an advanced composite prototype structure for the center wing section of the Lockheed C-130 aircraft. The TIBB was tested for downbending, upbending, torsion, and combined upbending and torsion load conditions to verify the design. The TIBB failed at 83 percent of design ultimate load for the combined upbending and torsion load condition. Current analytical and experimental results are described for a study of the mechanisms that led to the failure of the TIBB. Experimental results include load, strain, and deflection data. An analytical study was conducted of the TIBB structural response. Analytical results include strain and deflection results from a global analysis of the TIBB.
    Keywords: COMPOSITE MATERIALS
    Type: Second NASA Advanced Composites Technology Conference; p 99-111
    Format: text
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  • 8
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    Directional characteristics of lunar surface temperature from measurements by Surveyor I. (1967)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Lunar surface temperature directional characteristics measured by Surveyor 1, noting daytime temperature profile
    Keywords: SPACE SCIENCES
    Type: ; - QUANTUM ELECTRONIC
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  • 9
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    Computation of strain energy release rates for skin-stiffener debonds modeled with plate elements (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An efficient method for predicting the strength of debonded composite skin-stiffener configurations is presented. This method, which is based on fracture mechanics, models the skin and the stiffener with two-dimensional (2D) plate elements instead of three-dimensional (3D) solid elements. The skin and stiffener flange nodes are tied together by two modeling techniques. In one technique, the corresponding flange and skin nodes are required to have identical translational and rotational degrees-of-freedom. In the other technique, the corresponding flange and skin nodes are only required to have identical translational degrees-of-freedom. Strain energy release rate formulas are proposed for both modeling techniques. These formulas are used for skin-stiffener debond cases with and without cylindrical bending deformations. The cylindrical bending results are compared with plane-strain finite element results. Excellent agreement between the two sets of results is obtained when the second technique is used. Thus, from these limited studies, a preferable modeling technique for skin-stiffener debond analysis using plate elements is established.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 93-1501 , In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 3 (A93-33876 1; p. 1680-1692.
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  • 10
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    The axisymmetric response of cylindrical and hemispherical shells to time-dependent loading (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Dynamic response of complete cylindrical shell obtained by thin shell bending theory
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-572
    Format: application/pdf
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