1–20 von 96 Ergebnissen
|

    A cascade optimization strategy for solution of difficult multi-disciplinary design problems

    Patnaik, S.N. / Coroneos, R.M. / Hopkins, D.A. et al. | Tema Archiv | 1996
    successfully solved at least one third of the examples. It was realized that improvement to search directions and step lengths, available in the ten ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Reston

    A comparison of nonlinear techniques for structural health monitoring

    Gelman, Leonid M. / White, Paul R. / Hammond, Joe K. | Tema Archiv | 2006
    degree of nonlinearity and so be used as indicators of structural faults. Paper concentrates on the comparison of two techniques exploiting the ...
    Schlagwörter: SHM (structural health monitoring)

    A comparison of optimization formulations for design minimization of aircraft interior noise

    Crane, S.P. / Cunefare, K.A. / Engelstad, S.P. et al. | Tema Archiv | 1996
    were subject to upper and lower bounds on the design variables, the structural shell element thickness. All analyses were performed at a single ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Reston

    A coupled helicopter rotor/fuselage aeroelastic response model for ACSR

    Chiu, T. / Friedmann, P.P. | Tema Archiv | 1995
    dynamics and sensitivity. The role of non-structural mass for obtaining correct estimates for the lower fuselage frequencies is also addressed. The ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Washington

    A design scheme aimed at minimizing actuator and structural loads of a span morphing aircraft

    Boothe, Kenny | Tema Archiv | 2006
    . Performance and efficiency deteriorate rapidly as the airplane moves towards other portions of the flight envelope. One solution to this quandary is ...

    Advanced transparency development for USAF aircraft

    Bouchard, M.P. / Davisson, J.C. | Tema Archiv | 1993
    provides strain rate-dependent material properties, direct modeling of the bird, element and ply failure criteria, and rapid turnaround on ...

    Aeroelastic stability of smart trailing-edge flap helicopter rotors

    Shen, J. / Chopra, I. | Tema Archiv | 2001
    eigenanalysis of these homogeneous equations using a constant coefficient approximation approach and the Floquet method. The baseline correlation of ...
    Schlagwörter: intelligenter Werkstoff

    Aeromechanical stability of a bearingless composite rotor in forward flight

    Tracy, A.L. / Chopra, I. | Tema Archiv | 1993
    element based structural analysis including the effects of transverse shear and warping restraint is incorporated into the University of Maryland ...

    Aerothermoelastic stability of composite aircraft wings subjected to heat inputs

    Polli, Gian Mario / Mastroddi, Franco / Librescu, Liviu et al. | Tema Archiv | 2006
    of advanced composite materials and exposed to a heat flow generated by a laser beam impacting its deformed surface. The structural model is ...

    Algorithm for Generating the Pareto Optimal Set of Multiobjective Nonlinear Mixed-Integer Optimization Problems AIAA Paper 2007-1869 CD-ROM Number 7

    Mela, K. / Koski, J. / Silvennoinen, R. | British Library Conference Proceedings | 2007
    Schlagwörter: Structures , Structural dynamics , Materials

    Analysis of a rotor-stator stage using a two dimensional Euler aeroelastic solver

    Reddy, T.S.R. / Srivastava, R. | Tema Archiv | 1994
    coupled with a typical section structural model for each blade of the cascade in each row. The flutter and forced response characteristics are ...

    An analysis of flutter suppression using adaptive materials including power consumption

    Layton, J.B. | Tema Archiv | 1995
    Adaptive materials have shown promise for use in aeroelastic applications. One of these applications is flutter suppression. This paper ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Washington

    A new aeroelastic model for composite rotor blades with straight and swept tips

    Yuan, Kuo-An / Friedmann, P.P. / Vekatesan, C. | Tema Archiv | 1992
    An analytical model for predicting the aeroelastic behavior of composite rotor blades with straight and swept tips is presented. The blade ...

    A new sensitivity analysis for structural optimization of composite rotor blades

    Venkatesan, C. / Friedmann, P.P. / Yuan, Kuo-An | Tema Archiv | 1993
    This paper presents a detailed mathematical derivation of the sensitivity derivatives for the structural dynamic, aeroelastic stability and ...

    An examination of the gust response of a finite span wing with respect to structural and geometric parameters

    Layton, J.B. | Tema Archiv | 1995
    This paper examines the gust response of a finite span wing model with respect to structural and geometric parameters. Past studies into ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Washington

    An investigation of the total least-squares criteria in time domain based, parameter identification for flight flutter testing

    Pinkelman, J.K. / Batill, S.M. / Kehoe, M.W. | Tema Archiv | 1995
    Parameter identification of time series models for linear dynamic structural systems using the least squares and total least squares ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Washington
    Schlagwörter: Dynamik

    A nonlinear, coupled fluid-structural dynamics code for cryogenic refrigerators based on the Oxford split-stirling cycle design

    Jacoby, M.S. / Nast, T. | Tema Archiv | 1994
    paper describes the development of a nonlinear, coupled fluid-structural dynamics code which has been used for the basic mechanical design of ...

    A numerical investigation of the stability and post-flutter response of a 2D nonlinear airfoil in longitudinal atmospheric turbulence

    Poirel, D.C. / Price, S.J. | Tema Archiv | 1996
    The effect of longitudinal atmospheric turbulence on the flutter and post-flutter dynamics of a two-dimensional airfoil with a structural ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Reston

    A physical explanation of free play effects on the flutter response of an all movable control surface

    Pitt, D.M. | Tema Archiv | 1995
    are used during the simulation. One state model is used whenever the stabilator rotation angle is inside the free play zone, and another state ...
    Verlag: American Institute of Aeronautics and Astronautics (AIAA) , Washington

    Application of a weighted average surrogate approach to helicopter rotor blade vibration reduction

    Glaz, Bryan / Goel, Tushar / Liu, Li et al. | Tema Archiv | 2007
    vibration. The design variables consist of the cross-sectional dimensions of the structural member of the blade and non-structural masses. The ...