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  • 1
    Electronic Resource
    Electronic Resource
    Solution accuracies of finite element reentry heat transfer and thermal stress analyses of space shuttle orbiter (1988)
    Chichester [u.a.] : Wiley-Blackwell
    International Journal for Numerical Methods in Engineering 25 (1988), S. 517-543 
    Details
    ISSN: 0029-5981
    Keywords: Engineering ; Engineering General
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mathematics , Technology
    Notes: Accuracies of solutions (structural temperatures and thermal stresses) obtained from different finite element thermal and structural models set up for the space shuttle orbiter are compared and discussed. For studying the effect of element size on the solution accuracies of finite element heat transfer and thermal stress analyses of the orbiter, five structural performance and resizing (SPAR) thermal models and five NASA structural analysis (NASTRAN) structural models were set up for the orbiter wing midspan bay 3. The structural temperature distribution over the wing skin (lower and upper) surface of one bay was dome shaped and induced more severe thermal stresses in the chordwise direction than in the spanwise direction. The induced thermal stresses were extremely sensitive to slight variation in structural temperature distributions. Both internal convention and internal radiation were found to have equal effects on the orbiter structural temperatures. Minimum degrees of element fineness required for thermal and structural models for the orbiter to yield satisfactory solutions were established. In transient heat transfer analysis most of the computation time was consumed in the time-dependent temperature calculations and not in the radiation view-factor computations.
    Additional Material: 23 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/nme.1620250215
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    Paper (German National Licenses)
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  • 2
    Electronic Resource
    Electronic Resource
    Application of fracture mechanics and half-cycle theory to the prediction of fatigue life of aerospace structural components (1989)
    Springer
    International journal of fracture 39 (1989), S. 45-62 
    Details
    ISSN: 1573-2673
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Résumé On a analysé en application de la mécanique de rupture la vie en service de composants de structures aéronautiques soumis à une sollicitation cyclique aléatoire. A l'aide d'essais à la charge d'épreuve, on a établi les dimensions initiales d'une fissure aux points critiques de sollicitation, pour analyser sa croissance par fatigue. Les vitesses de croissance d'une fissure de fatigue dans le cas des charges aléatoires ont été calculées par la méthode des demi-cycles. On a mis au point une nouvelle expression pour calculer le nombre d'heures de vol résiduelles pour des éléments de structure. S'il résulte de cette nouvelle expression, ce nombre est beaucoup plus faible que celui prédit par les équations de vie résiduelle conventionnelles.
    Notes: Abstract The service life of aircraft structural components undergoing random stress cycling was analyzed by the application of fracture mechanics. The initial crack sizes at the critical stress points for the fatigue crack growth analysis were established through proof load tests. The fatigue crack growth rates for random stress cycles were calculated using the half-cycle method. A new equation was developed for calculating the number of remaining flights for the structural components. The number of remaining flights predicted by the new equation is much lower than that predicted by the conventional equation. This report describes the application of fracture mechanics and the half-cycle method to calculate the number of remaining flights for aircraft structural components.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00047439
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  • 3
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    Application of fracture mechanics and half-cycle theory to the prediction of fatigue life of aerospace structural components (1989)
    Springer
    Details
    Publication Date: 1989-03-01
    Print ISSN: 0376-9429
    Electronic ISSN: 1573-2673
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 4
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    Solution accuracies of finite element reentry heat transfer and thermal stress analyses of Space Shuttle Orbiter (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Accuracies of solutions (structural temperatures and thermal stresses) obtained from different thermal and structural FEMs set up for the Space Shuttle Orbiter (SSO) are compared and discussed. For studying the effect of element size on the solution accuracies of heat-transfer and thermal-stress analyses of the SSO, five SPAR thermal models and five NASTRAN structural models were set up for wing midspan bay 3. The structural temperature distribution over the wing skin (lower and upper) surface of one bay was dome shaped and induced more severe thermal stresses in the chordwise direction than in the spanwise direction. The induced thermal stresses were extremely sensitive to slight variation in structural temperature distributions. Both internal convention and internal radiation were found to have equal effects on the SSO.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 25; 517-543
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Application of fracture mechanics and half-cycle theory to the prediction of fatigue life of aerospace structural components (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The service life of aircraft structural components undergoing random stress cycling was analyzed by the application of fracture mechanics. The initial crack sizes at the critical stress points for the fatigue crack growth analysis were established through proof load tests. The fatigue crack growth rates for random stress cycles were calculated using the half-cycle method. A new equation was developed for calculating the number of remaining flights for the structural components. The number of remaining flights predicted by the new equation is much lower than that predicted by the conventional equation. This report describes the application of fracture mechanics and the half-cycle method to calculate the number of remaining flights for aircraft structural components.
    Keywords: STRUCTURAL MECHANICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Thermal stress analysis of space shuttle orbiter wing skin panel and thermal protection system (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preflight thermal stress analysis of the space shuttle orbiter wing skin panel and the thermal protection system (TPS) was performed. The heated skin panel analyzed was rectangular in shape and contained a small square cool region at its center. The wing skin immediately outside the cool region was found to be close to the state of elastic instability in the chordwise direction based on the conservative temperature distribution. The wing skin was found to be quite stable in the spanwise direction. The potential wing skin thermal instability was not severe enough to tear apart the strain isolation pad (SIP) layer. Also, the preflight thermal stress analysis was performed on the TPS tile under the most severe temperature gradient during the simulated reentry heating. The tensile thermal stress induced in the TPS tile was found to be much lower than the tensile strength of the TPS material. The thermal bending of the TPS tile was not severe enough to cause tearing of the SIP layer.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-88276 , H-1382 , NAS 1.15:88276
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Prediction of service life of aircraft structural components using the half-cycle method (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The service life of aircraft structural components undergoing random stress cycling was analyzed by the application of fracture mechanics. The initial crack sizes at the critical stress points for the fatigue-crack growth analysis were established through proof load tests. The fatigue-crack growth rates for random stress cycles were calculated using the half-cycle method. A new equation was developed for calculating the number of remaining flights for the structural components. The number of remaining flights predicted by the new equation is much lower than that predicted by the conventional equation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-86812 , H-1352 , NAS 1.15:86812
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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
  • 9
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    Effect of internal convection and internal radiation on the structural temperatures of Space Shuttle Orbiter (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Structural performance and resizing of the finite-element thermal analysis computer program was used in the reentry heat transfer analysis of the space shuttle orbiter. One midfuselage cross section and one midspan wing segment were selected to study the effects of internal convection and internal radiation on the structural temperatures. The effect of internal convection was found to be more prominent than that of internal radiation in the orbiter thermal analysis. Without these two effects, the calculated structural temperatures at certain stations could be as much as 45 to 90 percent higher than the measured values. By considering internal convection as free convection, the correlation between the predicted and measured structural temperatures could be improved greatly.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-100414 , H-1466 , NAS 1.15:100414
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Finite-element reentry heat-transfer analysis of space shuttle Orbiter (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat-transfer analysis of the space shuttle orbiter subjected to reentry aerodynamic heating. Three wing cross sections and one midfuselage cross section were selected for the thermal analysis. The predicted thermal protection system temperatures were found to agree well with flight-measured temperatures. The calculated aluminum structural temperatures also agreed reasonably well with the flight data from reentry to touchdown. The effects of internal radiation and of internal convection were found to be significant. The SPAR finite-element solutions agreed reasonably well with those obtained from the conventional finite-difference method.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-2657 , H-1236 , NAS 1.60:2657
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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