21–40 von 63 Ergebnissen
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    Unsteady force on slender aircraft with free vortices in inviscid flow

    Laat, T.W.G. de / Coene, R. | Tema Archiv | 2002
    inviscid flow, such as arise in the slender-body approximation of an aircraft. Zero-force curves for the classical vortex pair behind a circular ...

    Artificial Neural Network Modeling for Airline Disruption Management

    Kolawole Ogunsina / Wendy A Okolo | NTRS | 2022
    , existing platforms for airline disruption management (ADM) employ monolithic system design methods that rely on the creation of specific rules and ...
    Verlag: AIAA
    Schlagwörter: Aircraft Communications and Navigation

    Topological optimization of compliant adaptive wing structure

    Santer, M. / Pellegrino, S. | Tema Archiv | 2009
    Load-path-based topology optimization is used to synthesize a compliant adaptive aircraft wing leading edge, which deforms in a prescribed ...

    Comparison of surrogate models in a multidisciplinary optimization framework for wing design

    Paiva, Ricardo M. / Carvalho, Andre R.D. / Crawford, Curran et al. | Tema Archiv | 2010
    response surfaces, Kriging, and artificial neural networks. The results obtained from the solution of four different case studies based on aircraft ...

    Advanced test strategy for identification and characterization of nonlinearities of aerospace structures

    Göge, Dennis / Füllekrug, Michael / Link, Michael et al. | Tema Archiv | 2005
    testing. Also, the European aircraft industry is calling for a reduction of the testing times for prototypes without diminishing the accuracy of ...

    Modeling and simulation of nonlinear dynamics of flapping wing micro air vehicles

    Orlowski, Christopher T. / Girard, Anouck R. | Tema Archiv | 2011
    The derivation of the nonlinear dynamics of flapping wing micro air vehicles is presented. Simulation results investigate differences in ...

    Approximation of unsteady aerodynamics forces Q(k, M) by use of fuzzy techniques

    Hiliuta, Adrian / Botez, Ruxandra Mihaela / Brenner, Marty | Tema Archiv | 2005
    (subsonic regime) or a constant-pressure method (supersonic regime). To study the effects of the control laws on a flexible fly-by-wire aircraft ...

    Uncertainty quantification of structural response using evidence theory

    Bae, H.R. / Grandhi, R.V. / Canfield, R.A. | Tema Archiv | 2003
    probability theory may not be suitable for a large complex system such as an aircraft, in that the information is never complete because of lack of ...

    Analysis of conformable pressure vessels: introducing the multibubble

    Geuskens, F.J.J.M.M. / Bergsma, O.K. / Koussios, S. et al. | Tema Archiv | 2011
    This paper outlines the structural analysis of an articulated pressurizable structure termed the multibubble. The multibubble is a ...

    Aerodynamic optimization of a morphing airfoil using energy as an objective

    Namgoong, Howoong / Crossley, William A. / Lyrintzis, Anastasios S. | Tema Archiv | 2007
    Recent advances in materials science and actuation technologies have raised interest in morphing aircraft that can significantly change ...

    Numerical calculation of nonlinear aerodynamics of wing-body configurations

    Rusak, Z. / Wasserstrom, E. / Seginer, A. | Tema Archiv | 1983
    relevance to modern missiles and aircraft. Details of the calculations clarify the significant nonlinear contribution of the body to the aerodynamic ...

    Blade loss transient dynamic analysis of turbomachinery

    Stallone, M.J. / Gallardo, V. / Storace, A.F. et al. | Tema Archiv | 1983
    This paper reports on work completed to develop an analytical method for predicting the transient nonlinear response of a complete aircraft ...

    Active control of propeller-induced noise fields inside a flexible cylinder

    Lester, H.C. / Fuller, C.R. | Tema Archiv | 1990
    An active noise control model for reducing aircraft interior noise has been evaluated. The structural noise transmission properties of an ...

    Automatic control of laminar boundary-layer transition

    Nelson, P.A. / Wright, M.C.M. / Rioual, J.L. | Tema Archiv | 1997
    aircraft wings and engine nacelles. Suction may be most efficiently applied by using a number of independently controllable panels through which ...

    Noise control characteristics of synchrophasing, Part 2: experimental investigation

    Jones, J.D. / Fuller, C.R. | Tema Archiv | 1986
    A simplified cylindrical model of an aircraft fuselage is used to investigate the mechanisms of interior noise suppression of the ...

    New scheme for the computation of compressible flows

    Qamar, Adnan / Hasan, Nadeem / Sanghi, Sanjeev | Tema Archiv | 2006
    An important aspect of the design of supersonic aircraft is the minimization of aerodynamic and thermal loads onto the vehicle's surface ...

    Octree-advancing front method for generation of unstructured surface and volume meshes

    McMorris, H. / Kallinderis, Y. | Tema Archiv | 1997
    around a high-speed civil transport type of aircraft configuration using a hybrid prismatic/tetrahedral mesh. ...

    Parallelization of rotorcraft aerodynamics Navier-Stokes codes

    Ekici, K. / Lyrintzis, A.S. | Tema Archiv | 2002
    ability to predict the flow around helicopter rotors is vital for the control of high-speed losses, vibration, and noise. The advent of tilt-rotor ...

    Active aeroelastic control over a multisurface wing: modeling and wind-tunnel testing

    Gaspari, A. de / Ricci, S. / Riccobene, L. et al. | Tema Archiv | 2009
    a roll maneuver enhancement control system, now under development, so to be able to optimize the aircraft roll performances in terms of both ...

    Shape optimization methodology for reducing the sonic boom initial pressure rise

    Farhat, Charbel / Maute, Kurt / Argrow, Brian et al. | Tema Archiv | 2007
    A shape optimization methodology for reducing the initial shock pressure rise on the ground of a supersonic aircraft is presented. This ...