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  • 1
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    Buckling analysis and test correlation of high temperature structural panels (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: This paper focuses on the design, analysis, and test of a high temperature structural panel, constructed of Ti-6-4, subjected to a variety of thermal and mechanical load conditions. A follow-on panel, constructed of TMC, is also discussed in less detail. The design constraints and test set-up are discussed, as well as the test methods that were used: the grid shadow moire method and a single gage force stiffness method. The agreement between the test data and analysis for this test program provides confidence in the methods that are currently being used to design structures for hypersonic vehicles. The agreement also suggests that postbuckled strength may potentially be used to reduce the vehicle weight.
    Keywords: STRUCTURAL MECHANICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Techniques for hot structures testing (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Hot structures test techniques developed and applied by the Aerostructures Branch of the NASA Ames Research Center, Dryden Flight Research Facility, are presented. Topics covered include the data acquisition and control of testing, the quartz lamp heater systems, current strain and temperature sensors, and hot structures test techniques used to simulate the flight thermal environment in the laboratory.
    Keywords: QUALITY ASSURANCE AND RELIABILITY
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Thermal and structural tests of Rene 41 honeycomb integral-tank concept for future space transportation systems (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two flat 12 by 72 inch Rene 41 honeycomb sandwich panels were tested in a manner to produce combined thermal and mechanical longitudinal stresses that simulated those that would occur in a larger, more complex integral tank and fuselage structure of an earth to orbit vehicle. Elastic strains measured at temperatures below 400 F are compared with calculated values obtained from a linear elastic finite element analysis to verify the analytical model and to establish confidence in the calculated strains. Elastic strain measurement at higher temperatures (between 600 F and 1400 F), where strain measurement is more difficult and less certain, are also compared with calculated strains. Agreement between measured and calculated strains for the lower temperatures is good, but agreement for the higher temperatures is poor because of unreliable strain measurements. Test results indicate that an ascent and entry life cycle of 500 is attainable under high combined thermal and mechanical elastic strains.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-3145 , L-16752 , NAS 1.60:3145
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Buckling characteristics of hypersonic aircraft wing tubular panels (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The buckling characteristics of Rene 41 tubular panels installed as wing panels on a hypersonic wing test structure (HWTS) were determined nondestructively through use of a force/stiffness technique. The nondestructive buckling tests were carried out under different combined load conditions and different temperature environments. Two panels were subsequently tested to buckling failure in a universal tension compression testing machine. In spite of some data scattering because of large extrapolations of data points resulting from termination of the test at a somewhat low applied load, the overall test data correlated fairly well with theoretically predicted buckling interaction curves. The structural efficiency of the tubular panels was slightly higher than that of the beaded panels which they replaced.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-87756 , L-16128 , NAS 1.15:87756
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Buckling analysis and test correlation of hat stiffened panels for hypersonic vehicles (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The paper discusses the design, analysis, and test of hat stiffened panels subjected to a variety of thermal and mechanical load conditions. The panels were designed using data from structural optimization computer codes and finite element analysis. Test methods included the grid shadow moire method and a single gage force stiffness method. The agreement between the test data and analysis provides confidence in the methods that are currently being used to design structures for hypersonic vehicles. The agreement also indicates that post buckled strength may potentially be used to reduce the vehicle weight.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 90-5219
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Thermal stress analysis of space shuttle orbiter subjected to reentry aerodynamic heating (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A structural performance and resizing (SPAR) finite-element computer program and NASA structural analysis (NASTRAN) finite-element computer programs were used in the thermal stress analysis of the space shuttle orbiter subjected to reentry aerodynamic heating. A SPAR structural model was set up for the entire left wing of the orbiter, and NASTRAN structural models were set up for: (1) a wing segment located at midspan of the orbiter left wing, and (2) a fuselage segment located at midfuselage. The thermal stress distributions in the orbiter structure were obtained and the critical high thermal stress regions were identified. It was found that the thermal stresses induced in the orbiter structure during reentry were relatively low. The thermal stress predictions from the whole wing model were considered to be more accurate than those from the wing segment model because the former accounts for temperature and stress effects throughout the entire wing.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-88286 , H-1400 , NAS 1.15:88286
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Combined Loads Test Fixture for Thermal-Structural Testing Aerospace Vehicle Panel Concepts (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A structural test requirement of the National Aero-Space Plane (NASP) program has resulted in the design, fabrication, and implementation of a combined loads test fixture. Principal requirements for the fixture are testing a 4- by 4-ft hat-stiffened panel with combined axial (either tension or compression) and shear load at temperatures ranging from room temperature to 915 F, keeping the test panel stresses caused by the mechanical loads uniform, and thermal stresses caused by non-uniform panel temperatures minimized. The panel represents the side fuselage skin of an experimental aerospace vehicle, and was produced for the NASP program. A comprehensive mechanical loads test program using the new test fixture has been conducted on this panel from room temperature to 500 F. Measured data have been compared with finite-element analyses predictions, verifying that uniform load distributions were achieved by the fixture. The overall correlation of test data with analysis is excellent. The panel stress distributions and temperature distributions are very uniform and fulfill program requirements. This report provides details of an analytical and experimental validation of the combined loads test fixture. Because of its simple design, this unique test fixture can accommodate panels from a variety of aerospace vehicle designs.
    Keywords: Structural Mechanics
    Type: NASA/TM-2004-212039 , H-2488
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Flight vehicle thermal testing with infrared lamps (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The verification and certification of new structural material concepts for advanced high speed flight vehicles relies greatly on thermal testing with infrared quartz lamps. The basic quartz heater system characteristics and design considerations are presented. Specific applications are illustrated with tests that were conducted for the X-15, the Space Shuttle, and YF-12 flight programs.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-4336 , H-1779 , NAS 1.15:4336 , Structural Testing Technology at High Temperature Conference; Nov 04, 1991 - Nov 06, 1991; Dayton, OH; United States
    Format: application/pdf
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  • 9
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    Techniques for hot structures testing (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Hot structures testing have been going on since the early 1960's beginning with the Mach 6, X-15 airplane. Early hot structures test programs at NASA-Ames-Dryden focused on operational testing required to support the X-15 flight test program, and early hot structures research projects focused on developing lab test techniques to simulate flight thermal profiles. More recent efforts involved numerous large and small hot structures test programs that served to develop test methods and measurement techniques to provide data that promoted the correlation of test data with results from analytical codes. In Nov. 1988 a workshop was sponsored that focused on the correlation of hot structures test data with analysis. Limited material is drawn from the workshop and a more formal documentation is provided of topics that focus on hot structures test techniques used at NASA-Ames-Dryden. Topics covered include the data acquisition and control of testing, the quartz lamp heater systems, current strain and temperature sensors, and hot structures test techniques used to simulate the flight thermal environment in the lab.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-101727 , H-1664 , NAS 1.15:101727 , First Thermal Structures Conference; Nov 13, 1990 - Nov 15, 1990; Charlottesville, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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