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  • Open Access


    Time-Domain Analysis of Body Freedom Flutter Based on 6DOF Equation

    Zhehan Ji1, Tongqing Guo1,*, Di Zhou1, Zhiliang Lu1, Binbin Lyu2

    CMES-Computer Modeling in Engineering & Sciences, Vol.138, No.1, pp. 489-508, 2024, DOI:10.32604/cmes.2023.029088

    Abstract The reduced weight and improved efficiency of modern aeronautical structures result in a decreasing separation of frequency ranges of rigid and elastic modes. Particularly, a high-aspect-ratio flexible flying wing is prone to body freedom flutter (BFF), which is a result of coupling of the rigid body short-period mode with 1st wing bending mode. Accurate prediction of the BFF characteristics is helpful to reflect the attitude changes of the vehicle intuitively and design the active flutter suppression control law. Instead of using the rigid body mode, this work simulates the rigid body motion of the model by using the six-degree-of-freedom (6DOF)… More >

  • Open Access


    Aeroelastic Stabilities Analysis of a Transonic Fan Rotor NASA Rotor67

    Chunxiu Ji1, Dan Xie1,*

    The International Conference on Computational & Experimental Engineering and Sciences, Vol.25, No.3, pp. 1-1, 2023, DOI:10.32604/icces.2023.010329

    Abstract Blade flutter is a complex phenomenon that can lead to serious damage or failure of turbomachinery systems. Predicting and mitigating blade flutter is therefore an important aspect of the design and analysis of these systems[1]. In this paper, we present a comparative study of two representative methods for blade flutter predictions: the energy method and the computational fluid dynamics/computational structural dynamics (CFD/CSD) coupled time-domain method. The energy method is a decoupled approach that uses a simplified model of the blade and fluid-structure interaction to calculate the stability boundaries of the system[2]. The time-domain method, on the other hand, is a… More >

  • Open Access


    Geometrically Nonlinear Flutter Analysis Based on CFD/CSD Methods and Wind Tunnel Experimental Verification

    Changrong Zhang, Hongtao Guo, Li Yu, Binbin Lv, Hongya Xia*

    CMES-Computer Modeling in Engineering & Sciences, Vol.136, No.2, pp. 1743-1758, 2023, DOI:10.32604/cmes.2023.025528

    Abstract This study presents a high-speed geometrically nonlinear flutter analysis calculation method based on the high-precision computational fluid dynamics/computational structural dynamics methods. In the proposed method, the aerodynamic simulation was conducted based on computational fluid dynamics, and the structural model was established using the nonlinear finite element model and tangential stiffness matrix. First, the equilibrium position was obtained using the nonlinear static aeroelastic iteration. Second, the structural modal under a steady aerodynamic load was extracted. Finally, the generalized displacement time curve was obtained by coupling the unsteady aerodynamics and linearized structure motion equations. Moreover, if the flutter is not at a… More > Graphic Abstract

    Geometrically Nonlinear Flutter Analysis Based on CFD/CSD Methods and Wind Tunnel Experimental Verification

  • Open Access


    Post-Buckling and Panel Flutter of Pre-Heated Functionally Graded Plates

    Wei Xia1,2,*, Weilin Kong1, Yupeng Feng1, Shengping Shen1,2,*

    The International Conference on Computational & Experimental Engineering and Sciences, Vol.24, No.1, pp. 1-2, 2022, DOI:10.32604/icces.2022.08765

    Abstract Post-buckling and panel flutter behaviors of ceramic-metal FGM plates are studied for the skins of supersonic aircrafts. The effects of asymmetric material and temperature distributions, as well as the aerodynamic loads, on the thermo-mechanical response of FGM plates are discussed using finite element simulations. The aero-thermo-elastic model is established by using the simple power law material distribution, the rule of mixture for material effective properties, the nonlinear Fourier equations of heat conduction, von-Karman strain-displacement nonlinear relations, and the piston theory for supersonic aerodynamics. The finite element equations are established using the first-order shear deformable plate elements. The thermal post-buckling equilibrium… More >

  • Open Access


    Aeroelastic Analysis of a Supercritical Airfoil with Free-Play in Transonic Flow

    Shun He1,*, Gaowei Cui2

    The International Conference on Computational & Experimental Engineering and Sciences, Vol.24, No.1, pp. 1-4, 2022, DOI:10.32604/icces.2022.08753

    Abstract An investigation has been made into the nonlinear aeroelastic behavior of a supercritical airfoil (NLR 7301) considering free-play in transonic flow. Computational Fluid Dynamics (CFD) based on NavierStokes equations is implemented to calculate unsteady aerodynamic forces. A loosely coupled scheme with steady CFD and a graphic method are developed to obtain the static aeroelastic position. Frequency domain flutter solution with transonic aerodynamic influence coefficient is used to capture the linear flutter characteristic at different angle of attack (AoA). Time marching approach based on CFD is used to calculate the nonlinear aeroelastic response. The bifurcation diagram of pitching motion shows that… More >

  • Open Access


    Dynamic Meta-Modeling Method to Assess Stochastic Flutter Behavior in Turbomachinery

    Bowei Wang1, Wenzhong Tang1, Lukai Song2,3,*, Guangchen Bai3

    CMES-Computer Modeling in Engineering & Sciences, Vol.133, No.1, pp. 171-193, 2022, DOI:10.32604/cmes.2022.021123

    Abstract With increasing design demands of turbomachinery, stochastic flutter behavior has become more prominent and even appears a hazard to reliability and safety. Stochastic flutter assessment is an effective measure to quantify the failure risk and improve aeroelastic stability. However, for complex turbomachinery with multiple dynamic influencing factors (i.e., aeroengine compressor with time-variant loads), the stochastic flutter assessment is hard to be achieved effectively, since large deviations and inefficient computing will be incurred no matter considering influencing factors at a certain instant or the whole time domain. To improve the assessing efficiency and accuracy of stochastic flutter behavior, a dynamic meta-modeling… More >

  • Open Access


    Predicting Mobile Cross-Platform Adaptation Using a Hybrid Sem–ANN Approach

    Ali Alkhalifah*

    Computer Systems Science and Engineering, Vol.42, No.2, pp. 639-658, 2022, DOI:10.32604/csse.2022.022519

    Abstract Owing to constant changes in user needs, new technologies have been introduced to keep pace by building sustainable applications. Researchers and practitioners are keen to understand the factors that create an attractive user interface. Although the use of cross-platform applications and services is increasing, limited research has examined and evaluated cross-platforms for developing mobile applications for different operating systems. This study evaluates cross-platform features, identifying the main factors that help to create an attractive user adaptation when building sustainable applications for both Android and iOS. Flutter and React Native were selected so end-users could test their features using the cross-platform… More >

  • Open Access


    Aeroelastic Optimization of the High Aspect Ratio Wing with Aileron

    Mohammad Ghalandari1, Ibrahim Mahariq2, Farhad Ghadak3, Oussama Accouche2, Fahd Jarad4,5,*

    CMC-Computers, Materials & Continua, Vol.70, No.3, pp. 5569-5581, 2022, DOI:10.32604/cmc.2022.020884

    Abstract In aircraft wings, aileron mass parameter presents a tremendous effect on the velocity and frequency of the flutter problem. For that purpose, we present the optimization of a composite design wing with an aileron, using machine-learning approach. Mass properties and its distribution have a great influence on the multi-variate optimization procedure, based on speed and frequency of flutter. First, flutter speed was obtained to estimate aileron impact. Additionally mass-equilibrated and other features were investigated. It can deduced that changing the position and mass properties of the aileron are tangible following the speed and frequency of the wing flutter. Based on… More >

  • Open Access


    Thermally Induced Vibration Analysis of Flexible Beams Based on Isogeometric Analysis

    Jianchen Wu1, Yujie Guo1,*, Fangli Wang1,2

    CMES-Computer Modeling in Engineering & Sciences, Vol.128, No.3, pp. 1007-1031, 2021, DOI:10.32604/cmes.2021.016475

    Abstract Spacecraft flexible appendages may experience thermally induced vibrations (TIV) under sudden heating loads, which in consequence will be unable to complete their intended missions. Isogeometric analysis (IGA) utilizes, in an isoparametric concept, the same high order and high continuity non-uniform rational B-splines (NURBS) to represent both the geometry and the physical field of the structure. Compared to the traditional Lagrange polynomial based finite element method where only C0-continuity across elements can be achieved, IGA is geometrically exact and naturally fulfills the C1-continuity requirement of Euler–Bernoulli (EB) beam elements, therefore, does not need extra rotational degrees-of-freedom. In this paper, we present… More >

  • Open Access


    The Influence of Initial Deflection on Nonlinear Flutter Response of Functionally Graded Plates

    Wei Xia1,2,*, Kun Wang1, Haitao Yang1, Shengping Shen1

    The International Conference on Computational & Experimental Engineering and Sciences, Vol.21, No.2, pp. 27-27, 2019, DOI:10.32604/icces.2019.05197

    Abstract Panel flutter arises from the aeroelastic instability of the skin structures on the high-speed vehicles, usually in supersonic regime and combined with thermal environment. Unlike the catastrophic flutter of the wings, panel flutter tends to be treated as non-catastrophic one. The nonlinear panel flutter response is of great interest to find the fatigue loading spectra. Present work introduces an aeroelastic model for a thermal isolating panel made from functionally graded materials (FGMs). The Mindlin plate theory is employed to establish the structural equations, the first-order piston theory is adopted for the supersonic aerodynamic loads, and the von-Karman strain-displacement relation is… More >

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