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  • 1
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    Unknown
    Control of boundary layer transition location and plate vibration in the presence of an external acoustic field (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The experiment is aimed at controlling the boundary layer transition location and the plate vibration when excited by a flow and an upstream sound source. Sound has been found to affect the flow at the leading edge and the response of a flexible plate in a boundary layer. Because the sound induces early transition, the panel vibration is acoustically coupled to the turbulent boundary layer by the upstream radiation. Localized surface heating at the leading edge delays the transition location downstream of the flexible plate. The response of the plate excited by a turbulent boundary layer (without sound) shows that the plate is forced to vibrate at different frequencies and with different amplitudes as the flow velocity changes indicating that the plate is driven by the convective waves of the boundary layer. The acoustic disturbances induced by the upstream sound dominate the response of the plate when the boundary layer is either turbulent or laminar. Active vibration control was used to reduce the sound induced displacement amplitude of the plate.
    Keywords: STRUCTURAL MECHANICS
    Type: In: Structural dynamics: Recent advances; Proceedings of the 4th International Conference, Univ. of Southampton, United Kingdom, July 15-18, 1991 (A93-45104 18-39); p. 702-711.
    Format: text
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  • 2
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    VICONOPT - Program for exact vibration and buckling analysis or design of prismatic plate assemblies (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal (ISSN 0001-1452); 29; 1927
    Format: text
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  • 3
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    Structural dynamic and aeroelastic considerations for hypersonic vehicles (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Structural dynamic and aeroelastic considerations applicable to hypersonic vehicles are discussed. Emphasis is given to aerospace plane configurations. The definition of aerothermoelasticity and the operational flight environment are reviewed, and structural dynamic and aeroelastic areas of concern are individually discussed, including vibration, landing and taxiing, propellant dynamics, acoustics, lifting surface flutter, panel flutter, control surface buzz, buffeting, gust response, and static aeroelasticity. Recent research results from all-moveable delta-wing aerolastic studies, engine inlet lip aeroelastic analysis, and studies of thermal effects on vibration frequencies, aerodynamic heating effects on flutter, and active control of aeroelastic response are reviewed.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 91-1255
    Format: text
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  • 4
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    User manual for VICONOPT: An exact analysis and optimum design program covering the buckling and vibration of prismatic assemblies of flat in-plane loaded, anisotropic plates, with approximations for discrete supports, and transverse stiffeners (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computer program which is designed for efficient, accurate buckling and vibration analysis and optimum design of composite panels is described. The capabilities of the program are given along with detailed user instructions. It is written in FORTRAN 77 and is operational on VAX, IBM, and CDC computers and should be readily adapted to others. Several illustrations of the various aspects of the input are given along the example problems illustrating the use and application of the program.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-181966 , NAS 1.26:181966
    Format: application/pdf
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  • 5
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    Optimum design using VICONOPT, a buckling and strength constraint program for prismatic assemblies of anisotropic plates (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: A computer program for obtaining the optimum (least mass) dimensions of the kind of prismatic assemblies of laminated, composite plates which occur in advanced aerospace construction is described. Rigorous buckling analysis (derived from exact member theory) and a tailored design procedure are used to produce designs which satisfy buckling and material strength constraints and configurational requirements. Analysis is two to three orders of magnitude quicker than FEM, keeps track of all the governing modes of failure and is efficiently adapted to give sensitivities and to maintain feasibility. Tailoring encourages convergence in fewer sizing cycles than competing programs and permits start designs which are a long way from feasible and/or optimum. Comparisons with its predecessor, PASCO, show that the program is more likely to produce an optimum, will do so more quickly in some cases, and remains accurate for a wider range of problems.
    Keywords: STRUCTURAL MECHANICS
    Type: Computers & Structures (ISSN 0045-7949); 43; 4, Ma; 699-708
    Format: text
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