The Experts below are selected from a list of 831 Experts worldwide ranked by ideXlab platform

T H Hyde - One of the best experts on this subject based on the ideXlab platform.

  • on the prediction of elastic plastic Generalized load Displacement responses for tubular joints
    Journal of Strain Analysis for Engineering Design, 2000
    Co-Authors: S B Leen, T H Hyde
    Abstract:

    An energy-based method is presented for the prediction of the elastic-plastic force-Displacement and/or moment-rotation responses of tubular joints for arbitrary radial loading paths under the action of up to four combined forces and moments. The method is based on the results of a sample of load paths obtained from computational models or measured from experimental tests. The work is important in the context of the elastic-plastic behaviour of structures in general and in particular as a basis for the development of single elastic-plastic tubular joint elements. The method employs normality of the Generalized Displacement Vector to level hypersurfaces of total (elastic-plastic) complementary work.

S B Leen - One of the best experts on this subject based on the ideXlab platform.

  • on the prediction of elastic plastic Generalized load Displacement responses for tubular joints
    Journal of Strain Analysis for Engineering Design, 2000
    Co-Authors: S B Leen, T H Hyde
    Abstract:

    An energy-based method is presented for the prediction of the elastic-plastic force-Displacement and/or moment-rotation responses of tubular joints for arbitrary radial loading paths under the action of up to four combined forces and moments. The method is based on the results of a sample of load paths obtained from computational models or measured from experimental tests. The work is important in the context of the elastic-plastic behaviour of structures in general and in particular as a basis for the development of single elastic-plastic tubular joint elements. The method employs normality of the Generalized Displacement Vector to level hypersurfaces of total (elastic-plastic) complementary work.

Xia Wei - One of the best experts on this subject based on the ideXlab platform.

  • Dynamic Pressure Perturbation Method for Flutter Solution: the Mu-Omega Method
    2016
    Co-Authors: Gu Yingsong, Yang Zhichun, Wang Wei, Xia Wei
    Abstract:

    Applying perturbation to dynamic pressure in the nominal aeroleastic equation of motion, a Mu-Omega method is presented for flutter solution. Utilizing structured singular value mu as stability margin indicator, the method simply uses frequency domain aerodynamics to solve nominal flutter and divergence margin through frequency domain mu analysis. The error of flutter reduced frequency is selected as convergence criterion during airspeed iteration. Detailed algorithm is given and three numerical examples are solved for demonstration. It is shown that the Mu-Omega method has good convergence and high accuracy, and the flutter and divergence result from the Mu-Omega method correlate well with that of the p-k or KE method. Nomenclature M = Generalized mass matrix B = Generalized damping matrix K = Generalized stiffness matrix η = Generalized Displacement Vector k = reduced frequency b = semi chord µ = structured singular value s = Laplace variable V = airspeed Q = Generalized aerodynamic influence coefficient matrix ρ = air density q ∞ = dynamic pressure q0 = nominal dynamic pressure δq = perturbation operator to q0 Wq = weight value for ∆

Gu Yingsong - One of the best experts on this subject based on the ideXlab platform.

  • Dynamic Pressure Perturbation Method for Flutter Solution: the Mu-Omega Method
    2016
    Co-Authors: Gu Yingsong, Yang Zhichun, Wang Wei, Xia Wei
    Abstract:

    Applying perturbation to dynamic pressure in the nominal aeroleastic equation of motion, a Mu-Omega method is presented for flutter solution. Utilizing structured singular value mu as stability margin indicator, the method simply uses frequency domain aerodynamics to solve nominal flutter and divergence margin through frequency domain mu analysis. The error of flutter reduced frequency is selected as convergence criterion during airspeed iteration. Detailed algorithm is given and three numerical examples are solved for demonstration. It is shown that the Mu-Omega method has good convergence and high accuracy, and the flutter and divergence result from the Mu-Omega method correlate well with that of the p-k or KE method. Nomenclature M = Generalized mass matrix B = Generalized damping matrix K = Generalized stiffness matrix η = Generalized Displacement Vector k = reduced frequency b = semi chord µ = structured singular value s = Laplace variable V = airspeed Q = Generalized aerodynamic influence coefficient matrix ρ = air density q ∞ = dynamic pressure q0 = nominal dynamic pressure δq = perturbation operator to q0 Wq = weight value for ∆

Yang Zhichun - One of the best experts on this subject based on the ideXlab platform.

  • Dynamic Pressure Perturbation Method for Flutter Solution: the Mu-Omega Method
    2016
    Co-Authors: Gu Yingsong, Yang Zhichun, Wang Wei, Xia Wei
    Abstract:

    Applying perturbation to dynamic pressure in the nominal aeroleastic equation of motion, a Mu-Omega method is presented for flutter solution. Utilizing structured singular value mu as stability margin indicator, the method simply uses frequency domain aerodynamics to solve nominal flutter and divergence margin through frequency domain mu analysis. The error of flutter reduced frequency is selected as convergence criterion during airspeed iteration. Detailed algorithm is given and three numerical examples are solved for demonstration. It is shown that the Mu-Omega method has good convergence and high accuracy, and the flutter and divergence result from the Mu-Omega method correlate well with that of the p-k or KE method. Nomenclature M = Generalized mass matrix B = Generalized damping matrix K = Generalized stiffness matrix η = Generalized Displacement Vector k = reduced frequency b = semi chord µ = structured singular value s = Laplace variable V = airspeed Q = Generalized aerodynamic influence coefficient matrix ρ = air density q ∞ = dynamic pressure q0 = nominal dynamic pressure δq = perturbation operator to q0 Wq = weight value for ∆