Aeroelasticity

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Earl H. Dowell - One of the best experts on this subject based on the ideXlab platform.

  • enhancement to least square based approach for time domain unsteady aerodynamic approximation
    Journal of Aircraft, 2020
    Co-Authors: Frederico Ribeiro, Earl H. Dowell, Douglas Domingues Bueno
    Abstract:

    The modeling of different problems in Aeroelasticity requires a time-domain equation of motion, especially to design modern controllers and study nonlinear characteristics. Typically, unsteady aero...

  • mathematical Aeroelasticity a survey
    Journal | MESA, 2015
    Co-Authors: Igor Chueshov, Earl H. Dowell, Irena Lasiecka, Justin T Webster
    Abstract:

    A variety of models describing the interaction between flows and oscillating structures are discussed. The main aim is to analyze conditions under which structural instability (flutter) induced by a fluid flow can be suppressed or eliminated. The analysis provided focuses on effects brought about by: (i) different plate and fluid boundary conditions, (ii) various regimes for flow velocities:subsonic, transonic, or supersonic, (iii) different modeling of the structure which may or may not account for in-plane accelerations (full von Karman system), (iv) viscous effects, (v) an assortment ofmodels related to piston-theoretic model reductions, and (iv) considerations of axial flows (in contrast to so called normal flows). The discussion below is based on conclusions reached via a combination of rigorous PDE analysis, numerical computations, and experimental trials.

  • Aeroelasticity in civil engineering
    2015
    Co-Authors: Earl H. Dowell
    Abstract:

    Fluid-structure interaction occurs in civil engineering applications to flexible long span bridges and tall slender buildings. This chapter provides an authoritative account of current best practices and modeling methods.

  • some recent advances in nonlinear Aeroelasticity
    2015
    Co-Authors: Earl H. Dowell
    Abstract:

    This brings the discussion of nonlinear Aeroelasticity up to date. See the earlier discussion in Chap. 11. Much of the recent advances are based on newunderstanding of such subjects as limit cycle oscillations due to structural nonlinearities, including freeplay, and fluid nonlinearities associated with unsteadyseparated flow including self excited flow oscillations variously called buffet or non-synchronous vibration.

  • Aeroelasticity in Turbomachines
    A Modern Course in Aeroelasticity, 2014
    Co-Authors: Earl H. Dowell
    Abstract:

    The advent of the jet engine and the high performance axial-flow compressor toward the end of World War II focussed attention on certain aeroelastic problems in turbomachines.

Philip S. Beran - One of the best experts on this subject based on the ideXlab platform.

  • Uncertainty Quantification in Aeroelasticity
    Annual Review of Fluid Mechanics, 2017
    Co-Authors: Philip S. Beran, Bret Stanford, Christopher R. Schrock
    Abstract:

    It is important to account for uncertainties in aeroelastic response when designing and certifying aircraft. However, aeroelastic uncertainties are particularly challenging to quantify, since dynamic stability is a binary property (stable or unstable) that may be sensitive to small variations in system parameters. To correctly discern stability, the interactions between fluid and structure must be accurately captured. Such interactions involve an energy flow through the interface, which if unbalanced, can destablize the structure. With conventional computational techniques, the consequences of imbalance may require large simulation times to discern, and evaluating the dependence of stability on numerous system parameters can become intractable. In this chapter, the challenges in quantifying aeroelastic uncertainties will be explored and numerical methods will be described to decrease the difficulty of quantifying aeroelastic uncertainties and increase the reliability of aircraft structures subjected to airloads. A series of aeroelastic analyses and reliability studies will be carried out to illustrate key concepts.

  • Computational Nonlinear Aeroelasticity
    2008
    Co-Authors: Philip S. Beran, Richard D. Snyder
    Abstract:

    Abstract : This report documents the culmination of in-house work in the area of computational modeling techniques for Aeroelasticity. At the project onset, emphasis was given to the challenge of predicting flutter points for aircraft in the transonic regime. Methods based on bifurcation theory and reduced order modeling were developed and tested. This work helped to shape the activity of the aeroelastic community, and an international workshop in the subject area to be held in 2008 testifies to this achievement. Attention then turned to studying vehicles that might experience large structural deformations, such as high-altitude vehicles. Finally, computational methods have been investigated for the exploitation of aeroelastic interactions in the design of micro-air vehicles.

Christopher R. Schrock - One of the best experts on this subject based on the ideXlab platform.

  • Uncertainty Quantification in Aeroelasticity
    Annual Review of Fluid Mechanics, 2017
    Co-Authors: Philip S. Beran, Bret Stanford, Christopher R. Schrock
    Abstract:

    It is important to account for uncertainties in aeroelastic response when designing and certifying aircraft. However, aeroelastic uncertainties are particularly challenging to quantify, since dynamic stability is a binary property (stable or unstable) that may be sensitive to small variations in system parameters. To correctly discern stability, the interactions between fluid and structure must be accurately captured. Such interactions involve an energy flow through the interface, which if unbalanced, can destablize the structure. With conventional computational techniques, the consequences of imbalance may require large simulation times to discern, and evaluating the dependence of stability on numerous system parameters can become intractable. In this chapter, the challenges in quantifying aeroelastic uncertainties will be explored and numerical methods will be described to decrease the difficulty of quantifying aeroelastic uncertainties and increase the reliability of aircraft structures subjected to airloads. A series of aeroelastic analyses and reliability studies will be carried out to illustrate key concepts.

J.e. Jenkins - One of the best experts on this subject based on the ideXlab platform.

  • Aeroelasticity OF AN AIRFOIL TEST RIG
    Journal of Fluids and Structures, 1997
    Co-Authors: G.m. Graham, J.e. Jenkins
    Abstract:

    This paper describes an aeroelastic model for an airfoil test rig which is based on the mode superposition method for structural systems and linear airfoil theory for describing the unsteady airfoil loading. The model is applied to the case of an airfoil undergoing rapid, small amplitude step-like maneuvers. The motivation for these tests was an interest in measuring airfoil indicial responses, which are defined as the loading response to a step input in angle of attack. Due to the rapid starting and stopping of the airfoil rig, the structure may experience significant aeroelastic deformations. These may arise from inertial as well as aerodynamic effects. The present model may be of general interest as a means for quantifying and correcting aeroelastic effects in tow tank and wind tunnel test facilities.

Ren Jianting - One of the best experts on this subject based on the ideXlab platform.

  • A rapid Aeroelasticity optimization method based on the stiffness characteristics
    'Scipedia S.L.', 2019
    Co-Authors: Yuan Zhe, Huo Shihui, Ren Jianting
    Abstract:

    A rapid Aeroelasticity optimization method based on the stiffness characteristics was proposed in the present study. Large time expense in static Aeroelasticity analysis based on traditional time domain Aeroelasticity method is solved. Elastic axis location and torsional stiffness are discussed firstly. Both torsional stiffness and the distance between stiffness center and aerodynamic center have a direct impact on divergent velocity. The divergent velocity can be adjusted by changing the correlative structural parameters. The relation between structural parameters and divergent velocity is introduced to Aeroelasticity optimization design as a constraint condition. After optimization, the structural and aerodynamic characteristics have a large improvement while satisfying the constraint conditions. The optimization method can be well used in high aspect ratio wing and has great computational efficiency.Peer Reviewe

  • A rapid Aeroelasticity optimization method based on the stiffness characteristics
    2019
    Co-Authors: Yuan Zhe, Huo Shihui, Ren Jianting
    Abstract:

    A rapid Aeroelasticity optimization method based on the stiffness characteristics was proposed in the present study. Large time expense in static Aeroelasticity analysis based on traditional time domain Aeroelasticity method is solved. Elastic axis location and torsional stiffness are discussed firstly. Both torsional stiffness and the distance between stiffness center and aerodynamic center have a direct impact on divergent velocity. The divergent velocity can be adjusted by changing the correlative structural parameters. The relation between structural parameters and divergent velocity is introduced to Aeroelasticity optimization design as a constraint condition. After optimization, the structural and aerodynamic characteristics have a large improvement while satisfying the constraint conditions. The optimization method can be well used in high aspect ratio wing and has great computational efficiency