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  • 1
    facet.materialart.
    Unknown
    Analysis of wing-body interaction flutter for a preliminary space shuttle design (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Subsonic flutter analyses for a preliminary space shuttle design were performed to determine the effect of wing-body aerodynamic interaction on the vehicle flutter speed. It was found that the proximity of the large bodies of the shuttle to the wing reduces critical flutter speed by 11%. Aerodynamic reflection off the bodies is the dominant interaction effect while aerodynamic forces caused by body motion are of secondary importance in most cases. The analyses employed a doublet-lattice representation of the space shuttle, where in the wing and body surfaces were modeled by a lattice of nonplanar lifting surface elements. Axial singularities were introduced to account for body incidence, volume, and camber (slender body) effects. A series of studies on the placement and number of these elements was performed to ensure convergence of the results.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2429
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Design and fabrication of realistic adhesively bonded joints (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Eighteen bonded joint test specimens representing three different designs of a composite wing chordwise bonded splice were designed and fabricated using current aircraft industry practices. Three types of joints (full wing laminate penetration, two side stepped; midthickness penetration, one side stepped; and partial penetration, scarfed) were analyzed using state of the art elastic joint analysis modified for plastic behavior of the adhesive. The static tensile fail load at room temperature was predicted to be: (1) 1026 kN/m (5860 1b/in) for the two side stepped joint; (2) 925 kN/m (5287 1b/in) for the one side stepped joint; and (3) 1330 kN/m (7600 1b/in) for the scarfed joint. All joints were designed to fail in the adhesive.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-166099 , NAS 1.26:166099
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Characterization of graphite/epoxy laminates for aeroelastic tailoring (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A study of interaction between wing bending and twist by graphite/epoxy anisotropic laminates used in aircraft wing skins is presented. The laminates were used as covers for subscale box beams supported as a cantilever and tested in tip shear and tip torque, measuring beam response with a reflected light technique. The results indicated that the in-plane stiffness properties of anisotropic laminates can be predicted if the layer properties of the composite materials are known; thus, the coupled bending/twist response of wing type structures made from these laminates can be determined provided the limits of the laminate linear behavior are not significantly exceeded.
    Keywords: COMPOSITE MATERIALS
    Type: Composite materials: Testing and design; Mar 20, 1978 - Mar 22, 1978; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental investigation of orthotropic panel flutter at arbitrary yaw angles, and comparison with theory (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flutter characteristics for yaw angles between 15 deg and 90 deg were determined experimentally for two types of corrugation-stiffened panels: those with weak twisting stiffness and those with strong twisting stiffness. By mounting the panels on a remotely controlled turntable, good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Flutter tests were conducted at M = 2 and M = 1.6. Before testing, vibration tests and analyses were also performed. The experimental flutter data is compared with flutter theory for orthotropic panels utilizing quasi-steady aerodynamics. Five different corrugated panels were tested consisting of one single skin panel having a length-to-width ratio of 5 on clamped supports and four different square double skin panels on discrete flexible supports. The investigation indicated that flutter speed for corrugated panels is highly dependent on yaw angle. Reasonable flutter correlation between analysis and test was obtained for moderate yaw angles, but extreme sensitivity to structural parameters made the correlation at large yaw angles uncertain.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2265
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Space Shuttle flutter as affected by wing-body aerodynamic interaction (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In the NASA Langley Research Center 26-inch transonic blowdown wind-tunnel, flutter speeds were measured on 1/80-th scale semispan models of the orbiter wing, the complete Space Shuttle, and intermediate component combinations. Using the doublet lattice method combined with slender body theory to calculate unsteady aerodynamic forces, subsonic flutter speeds were computed for comparison. Aerodynamic interaction was found by test and analysis to raise the flutter speed in some configurations while lowering it in others. Although at Mach number less than 0.7, predicted speeds correlated to within 6% of those measured, rapid deterioration of the agreement occurred at higher subsonic Mach numbers, especially on the more complicated configurations. Additional analysis showed that aerodynamic forces arising from body flexibility potentially can have a large effect on flutter speed, but that the current shuttle design is not so affected.
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 74-363 , Structures, Structural Dynamics and Materials Conference; Apr 17, 1974 - Apr 19, 1974; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Orthotropic panel flutter at arbitrary yaw angles - Experiment and correlation with theory. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Experimental flutter boundaries were obtained for yaw angles between 15 and 90 deg at Mach numbers 2 and 1.6 for panels mounted on a remotely controlled turntable. Good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Two types of specimens were tested: a single-sheet corrugated panel having a length-to-width ratio of 5 on clamped supports, and several square doubly-corrugated panels on various flexible supports. Calculated flutter speeds based on quasi-steady aerodynamics are compared to experimental data.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 73-192 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
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