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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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    Honeycomb sandwich structure for future space transportation systems with integral cryogenic tankage (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2029, Accession no. A82-30084
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 246-252
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of measured and calculated temperatures for a Mach 8 hypersonic wing test structure (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Structural temperatures were measured on a hypersonic wing test structure during a heating test that simulated a Mach 8 thermal environment. Measured data are compared to design calculations and temperature predictions obtained from a finite-difference thermal analysis.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85918 , H-1271 , A-85137 , NAS 1.15:85918
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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    Loading tests of a wing structure for a hypersonic aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Room-temperature loading tests were conducted on a wing structure designed with a beaded panel concept for a Mach 8 hypersonic research airplane. Strain, stress, and deflection data were compared with the results of three finite-element structural analysis computer programs and with design data. The test program data were used to evaluate the structural concept and the methods of analysis used in the design. A force stiffness technique was utilized in conjunction with load conditions which produced various combinations of panel shear and compression loading to determine the failure envelope of the buckling critical beaded panels The force-stiffness data did not result in any predictions of buckling failure. It was, therefore, concluded that the panels were conservatively designed as a result of design constraints and assumptions of panel eccentricities. The analysis programs calculated strains and stresses competently. Comparisons between calculated and measured structural deflections showed good agreement. The test program offered a positive demonstration of the beaded panel concept subjected to room-temperature load conditions.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1596 , H-1046
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Development of Rene' 41 honeycomb structure as an integral cryogenic tankage/fuselage concept for future space transportation systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The status of the structural development of an integral cryogenic-tankage/hot-fuselage concept for future space transportation systems (STS) is discussed. The concept consists of a honeycomb sandwich structure which serves the combined functions of containment of cryogenic fuel, support of vehicle loads, and thermal protection from an entry heating environment. The inner face sheet is exposed to a cryogenic (LH2) temperature of -423 F during boost; and the outer face sheet, which is slotted to reduce thermal stress, is exposed to a maximum temperature of 1400 F during a high altitude, gliding entry. A fabrication process for a Rene' 41 honeycomb sandwich panel with a core density less than 1 percent was developed which is consistent with desirable heat treatment processes for high strength.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-83306 , NAS 1.15:83306 , AIAA PAPER 82-0653
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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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    NASA TECHNICAL REPORTS
  • 9
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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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    NASA TECHNICAL REPORTS
  • 10
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    Evaluation of an infrared heating simulation of a Mach 4.63 flight on an X 15 horizontal stabilizer (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Infrared heating simulation of Mach 4.63 flight on X-15 horizontal stabilizer
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-5403
    Format: application/pdf
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