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  • 1
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    Tests of beaded and tubular structural panels (1978)
    In:  CASI
    Details
    Publication Date: 2006-06-12
    Description: Two efficient concepts built from curved elements were identified, and a data base for tubular panels was developed. The tubular panel failure modes were understood, and the data base for these panels indicated that their performance can be predicted. The concepts are currently being tested in a realistic builtup structure; 157 room temperature tests and 67 hot tests were made with no structural failures, although all of these tests were not at the design load of the structure.
    Keywords: STRUCTURAL MECHANICS
    Type: Recent Advan. in Structures for Hypersonic Flight, Pt. 2; p 538-576
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Dryden Flight Research Center hot structures research (1978)
    In:  CASI
    Details
    Publication Date: 2006-06-13
    Description: The facilities, testing techniques, and design methods are described for NASA Dryden Flight Research Center. High temperature strain gage technology, realistic flight hardware fabrication, and structural analysis are discussed. A considerable amount of experimental work on hot structure concepts for hypersonic vehicles was performed; all the work is not complete, and there are still problem areas that need to be resolved.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Recent Advan. in Structures for Hypersonic Flight, Pt. 2; p 707-750
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Buckling behavior of Rene 41 tubular panels for a hypersonic aircraft wing (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The buckling characteristics of Rene 41 tubular panels for a hypersonic aircraft wing were investigated. The panels were repeatedly tested for buckling characteristics using a hypersonic wing test structure and a universal tension/compression testing machine. The nondestructive buckling tests were carried out under different combined load conditions and in different temperature environments. The force/stiffness technique was used to determine the buckling loads of the panels. In spite of some data scattering resulting from large extrapolations of the data-fitting curve (because of the termination of applied loads at relatively low percentages of the buckling loads), the overall test data correlate fairly well with theoretically predicted buckling interaction curves. Also, the structural efficiency of the tubular panels was found to be slightly higher than that of beaded panels.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 86-0978
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Experiments to study strain gage load calibrations on a wing structure at elevated temperatures (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Laboratory experiments were performed to study changes in strain-gage bridge load calibrations on a wing structure heated to temperatures of 200 F, 400 F, and 600 F. Data were also obtained to define the experimental repeatability of strain-gage bridge outputs. Experiments were conducted to establish the validity of the superposition of bridge outputs due to thermal and mechanical loads during a heating simulation of Mach 3 flight. The strain-gage bridge outputs due to load cycle at each of the above temperature levels were very repeatable. A number of bridge calibrations were found to change significantly as a function of temperature. The sum of strain-gage bridge outputs due to individually applied thermal and mechanical loads compared well with that due to combined or superimposed loads. The validity of superposition was, therefore, established.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-7390 , H-763
    Format: application/pdf
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  • 5
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    Experimental investigation of Mach 3 cruise heating simulations on a representative wing structure for flight loads measurement (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Radiant heating experiments were performed in the laboratory on an instrumented multispar wing structure to investigate: (1) how accurately the structural temperatures of a Mach 3 cruise-flight profile could be simulated, (2) what the effects of the heating and heating inaccuracies would be on the responses of strain-gage bridges installed on the structure, and (3) how these responses would affect flight loads measurements. Test temperatures throughout the structure agreed well with temperatures calculated for a Mach 3 profile. In addition, temperatures produced by two identical tests were repeatable to less than + or -6 K deg. Thermally induced strain-gage-bridge responses were large enough to be detrimental to a high-speed flight loads program with a goal of establishing aerodynamic loads (exclusive of thermal loads). It was shown that heating simulation can be used effectively for thermal calibration (that is, to provide corrections for a high-temperature environment), and that thermal calibration may not be needed if the simulation data are used to carefully select bridges and load equations.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6749 , H-676
    Format: application/pdf
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  • 6
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    A study of the accuracy of a flight-heating simulation and its effect on load measurement (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: X-15 flight heating simulation accuracy tested and inaccuracy effects on flight load strain gage responses
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-5741 , H-597
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Buckling behavior of Rene 41 tubular panels for a hypersonic aircraft wing (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The buckling characteristics of Rene 41 tubular panels for a hypersonic aircraft wing were investigated. The panels were repeatedly tested for buckling characteristics using a hypersonic wing test structure and a universal tension/compression testing machine. The nondestructive buckling tests were carried out under different combined load conditions and in different temperature environments. The force/stiffness technique was used to determine the buckling loads of the panel. In spite of some data scattering, resulting from large extrapolations of the data fitting curve (because of the termination of applied loads at relatively low percentages of the buckling loads), the overall test data correlate fairly well with theoretically predicted buckling interaction curves. Also, the structural efficiency of the tubular panels was found to be slightly higher than that of beaded panels.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-86798 , H-1327 , NAS 1.15:86798 , AIAA PAPER 86-0978 , AIAA/ASME/ASCE/AHS Structures, Structural Dynamics and Materials Conference; May 19, 1986 - May 21, 1986; San Antonio, TX; United States
    Format: application/pdf
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  • 8
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    Experimental investigation of the buckling characteristics of a beaded skin panel for a hypersonic aircraft - Including comparisons with finite element and classical analyses (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results of a compression test of a beaded panel intended for a proposed hypersonic aircraft are presented. The panel was tested to failure at room temperature to determine its buckling characteristics, in particular, to study the buckling caused by pure compression. The boundary conditions of the panel simulated as nearly as possible a wing mounted condition. Strain, out-of-plane deflection, and load data were measured, and elastic buckling strength as well as mode shapes of the panel were determined. Application of the moire technique is described.
    Keywords: STRUCTURAL MECHANICS
    Type: ASME PAPER 78-WA/AERO-3 , American Society of Mechanical Engineers, Winter Annual Meeting; Dec 10, 1978 - Dec 15, 1978; San Francisco, CA
    Format: text
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