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学者姓名：张伟
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Abstract ：
Negative Poisson's ratio materials are increasingly used in the design of vibration isolation bases due to their unique tensile properties. In this paper, based on the expansion feature of the negative Poisson's ratio re-entrant structure, the influence of the size of the re-entrant structure within a single structure was analyzed, and a honeycomb base was designed with a negative Poisson's ratio re-entrant structure. A new modeling method for the honeycomb base is proposed. In the modeling process, the honeycomb base was analyzed according to its symmetry using the Lagrange equation for base modeling and the finite element consistent mass matrix was introduced to simplify the calculation. The vibration isolation performance of the honeycomb base was evaluated by vibration level difference. COMSOL software was used to simulate and analyze the cellular base in order to verify the correctness of the results obtained from numerical modeling. In conclusion, the honeycomb base had a vibration isolation effect on external excitation in the vertical direction of the base. Furthermore, the vibration isolation performance of the base was greatly related to the wall thickness and Poisson's ratio of the re-entrant structure.
Keyword ：
model model vibration isolation vibration isolation negative Poisson's ratio negative Poisson's ratio Lagrange equation Lagrange equation
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| GB/T 7714 | Pan, Kun , Zhang, Wei , Ding, Jieyu . Negative Poisson's Ratio Re-Entrant Base Modeling and Vibration Isolation Performance Analysis [J]. | SYMMETRY-BASEL , 2022 , 14 (7) . |
| MLA | Pan, Kun 等. "Negative Poisson's Ratio Re-Entrant Base Modeling and Vibration Isolation Performance Analysis" . | SYMMETRY-BASEL 14 . 7 (2022) . |
| APA | Pan, Kun , Zhang, Wei , Ding, Jieyu . Negative Poisson's Ratio Re-Entrant Base Modeling and Vibration Isolation Performance Analysis . | SYMMETRY-BASEL , 2022 , 14 (7) . |
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Abstract ：
The wind turbine blade is commonly treated as a non-uniform beam because of its high aspect ratio. The bend-twist coupled vibrations of the wind turbine blade occur when there exist the misalignments among the shear center, neutral axis and pressure center in the blade cross-section. The differential governing equations of motion for the rotating wind turbine blade are derived by Hamilton principle and solved by the transferred differential transformation method (TDTM). Due to the rotations, three terms, namely the tension, centrifugal and gyroscopic forces, are distinctively summarized and taken into ac-count in the proposed model. The natural frequencies obtained by the TDTM are compared with both experimental and numerical simulations to validate the effectiveness of the proposed solving method. The influences of the tension, centrifugal and gyroscopic forces on the natural frequencies are investi-gated for the wind turbine blade. The mode veering phenomenon is found and explained by using the complex mode decomposition theory. The phase differences among the flap-wise, edge-wise and torsional motions are also explored by observing the whirling orbits at the blade tip. (C) 2022 Elsevier Ltd. All rights reserved.
Keyword ：
Centrifugal effect Centrifugal effect Bend-twist coupling Bend-twist coupling Rotating wind turbine blade Rotating wind turbine blade Differential transformation method Differential transformation method Mode veering Mode veering
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| GB/T 7714 | Zhou, J. W. , Zhang, W. , Jiang, X. et al. Investigation on dynamics of rotating wind turbine blade using transferred differential transformation method [J]. | RENEWABLE ENERGY , 2022 , 188 : 96-113 . |
| MLA | Zhou, J. W. et al. "Investigation on dynamics of rotating wind turbine blade using transferred differential transformation method" . | RENEWABLE ENERGY 188 (2022) : 96-113 . |
| APA | Zhou, J. W. , Zhang, W. , Jiang, X. , Zhai, E. D. . Investigation on dynamics of rotating wind turbine blade using transferred differential transformation method . | RENEWABLE ENERGY , 2022 , 188 , 96-113 . |
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Abstract ：
In this paper, the natural vibration of an elastically supported porous truncated joined conical-conical shell (JCCS) is studied. The elastic support is achieved by using artificial spring technology. Four types of the metal foam porous distribution are presented, i.e. the uniform distribution along the radial direction and three other types of the gradient distribution. By applying Hamilton principle and the first order shear deformation theory (FSDT), dynamic equations of motion of the JCCS in the form of partial differential are derived. Considering the elastically supported boundary conditions, displacements continuity conditions and forces continuity conditions at the joining section of the coupling conical shell, partial differential equations used to describe this dynamic system are simplified into a set of algebraic equations by utilizing the generalized differential quadrature method (GDQM), in which the trigonometric function is used in the circumferential direction, while in meridian direction the DQ is applied. To obtain the natural vibration characteristic of the JCCS, the eigenvalue solving technology is utilized. The validation and convergence of the theoretical formulation are confirmed by comparison studies. Influences of boundary conditions, the spring stiffness, the geometric and material parameters on natural frequencies and mode shapes of the JCCS with two particular elastic boundary conditions are studied in detail.(c) 2022 Elsevier Masson SAS. All rights reserved.
Keyword ：
Arbitrary elastic boundary Arbitrary elastic boundary Porous Porous Joined conical-conical shell Joined conical-conical shell Natural vibration Natural vibration Generalized differential quadrature method Generalized differential quadrature method
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| GB/T 7714 | Li, H. , Hao, Y. X. , Zhang, W. et al. Natural vibration of an elastically supported porous truncated joined conical-conical shells using artificial spring technology and generalized differential quadrature method [J]. | AEROSPACE SCIENCE AND TECHNOLOGY , 2022 , 121 . |
| MLA | Li, H. et al. "Natural vibration of an elastically supported porous truncated joined conical-conical shells using artificial spring technology and generalized differential quadrature method" . | AEROSPACE SCIENCE AND TECHNOLOGY 121 (2022) . |
| APA | Li, H. , Hao, Y. X. , Zhang, W. , Liu, L. T. , Yang, S. W. , Cao, Y. T. . Natural vibration of an elastically supported porous truncated joined conical-conical shells using artificial spring technology and generalized differential quadrature method . | AEROSPACE SCIENCE AND TECHNOLOGY , 2022 , 121 . |
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Abstract ：
In this paper, the active damping control of the porous metal foam truncated conical shell with smart material macro fiber composite (MFC) is studied. Suppose the shell has arbitrary elastic supported edges, and is subjected to the impact loadings. The elastic supported edges can be achieved by virtual spring technique. Adopting the elastic constraint boundary condition, various classical boundaries can be easily realized by varying the value of the spring stiffnesses. Along the thickness direction, there are three types of porosity distributions of truncated conical shell being considered, and they are nonuniform symmetric, uniform and nonuniform asymmetric distribution, respectively. The sensor layer MFC-d31 and the actuator layer MFC-d33 are applied in the vibration control system. According to the first order shear deformation theory (FSDT) and energy principle, the dynamic equation of the system under electrostatic-mechanical coupling is derived. Then it is discretized into ordinary differential equation by generalized differential quadrature method (GDQM). The output charge applied to the sensor can be solved by integral quadrature method (IQM). The convergence and validation of the formulation and numerical calculation are studied by the comparisons between the present solutions and those from the literatures, ANSYS and COMSOL for the truncate conical shell with classical boundary conditions, respectively. Suppose the impact loadings acting on the porous truncated conical shell are step loading and decreasing loading, respectively. The velocity negative feedback approach is employed to diminish the amplitude of the transient response and achieve the active damping control. Then the effects of control gain, external excitation, semi-vertex angle and spring stiffness on the transient response control of the conical shell are studied in detail.
Keyword ：
Integral quadrature method Integral quadrature method Active vibration control Active vibration control Smart porous conical shell Smart porous conical shell Generalized differential quadrature method Generalized differential quadrature method Transient response Transient response
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| GB/T 7714 | Hao, Y. X. , Li, H. , Zhang, W. et al. Active vibration control of smart porous conical shell with elastic boundary under impact loadings using GDQM and IQM [J]. | THIN-WALLED STRUCTURES , 2022 , 175 . |
| MLA | Hao, Y. X. et al. "Active vibration control of smart porous conical shell with elastic boundary under impact loadings using GDQM and IQM" . | THIN-WALLED STRUCTURES 175 (2022) . |
| APA | Hao, Y. X. , Li, H. , Zhang, W. , Ge, X. S. , Yang, S. W. , Cao, Y. T. . Active vibration control of smart porous conical shell with elastic boundary under impact loadings using GDQM and IQM . | THIN-WALLED STRUCTURES , 2022 , 175 . |
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Abstract ：
The nonlinear vibrations and dynamic snap-through behaviors are studied for a four-corner simply supported bistable asymmetric laminated composite square shell under the foundation excitation by using the theoretical, Abaqus finite element (FE) and experiment approaches. The first-order shear deformation shell theory and Hamilton principle are adopted to derive the partial differential governing equations of motion. A novel type of nonlinear strain-displacement relations is given by Sander's strain. Galerkin approach is utilized to discretize the partial differential equations of motion into a three-degree-of-freedom system. The natural frequencies and vibration modes of the bistable shell are calculated by using Chebyshev polynomial method. The nonlinear vibrations and dynamic snap-through are investigated by using the maximum Lyapunov exponent, bifurcation diagrams, time histories, phase portraits, 3D phase portraits and Poincare maps. The theoretical results of the vibrations are well compared with those of the FE and experiment. The effects of the excitation and structural parameters on the dynamic snap through and nonlinear vibrations are fully discussed. The influences of the initial radius of the curvature on the critical load of the dynamic snap-through behaviors and rule of the chaotic vibrations are analyzed for the bistable asymmetric laminated composite shell.
Keyword ：
Nonlinear vibrations Nonlinear vibrations Four-corner simply supported bistable Four-corner simply supported bistable Dynamic snap-through Dynamic snap-through asymmetric laminated composite shell asymmetric laminated composite shell Double-well chaotic vibrations Double-well chaotic vibrations
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| GB/T 7714 | Wu, M. Q. , Zhang, W. , Chronopoulos, D. . Nonlinear vibrations and dynamic snap-through behaviors of four-corner simply supported bistable asymmetric laminated composite square shell [J]. | MECHANICAL SYSTEMS AND SIGNAL PROCESSING , 2022 , 173 . |
| MLA | Wu, M. Q. et al. "Nonlinear vibrations and dynamic snap-through behaviors of four-corner simply supported bistable asymmetric laminated composite square shell" . | MECHANICAL SYSTEMS AND SIGNAL PROCESSING 173 (2022) . |
| APA | Wu, M. Q. , Zhang, W. , Chronopoulos, D. . Nonlinear vibrations and dynamic snap-through behaviors of four-corner simply supported bistable asymmetric laminated composite square shell . | MECHANICAL SYSTEMS AND SIGNAL PROCESSING , 2022 , 173 . |
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Abstract ：
A robust control method is developed to suppress the vibrations of the functionally graded carbon nanotube-reinforced (FG-CNTR) piezoelectric laminated composite cantilever plate subjected to the aerodynamic force and thermal environment. The distributions of the carbon nanotubes (CNTs) in the entire plate thickness are classified as the functionally graded (FG) or uniform distributions (UD). The effective material properties are obtained using the rule of mixtures. The classic laminated composite plate theory and Hamilton principle are used to establish the governing equations of motion for the FG-CNTR laminated composite cantilever plate under combined the aerodynamic force and thermal environment. Galerkin method is used to obtain a two-degree-of-freedom ordinary differential control equation. To actively suppress the vibration, the piezoelectric patches are used as the actuators and sensors which are attached to the upper and lower surfaces of the FG-CNTR laminated composite cantilever plate. A full-dimensional state observer is introduced to design the robust controller. To verify the efficiency of the control strategy, a comparison between the robust controller and velocity feedback controller (VFC) indicates that the robust controller has better control efficiency than the VFC. The effects of the CNT distribution, CNT volume fraction, temperature and aspect ratio on the dynamic behaviors of the laminated composite plates are studied. The effectiveness and accuracy of the proposed robust controller are verified through numerical simulations under different cases.
Keyword ：
Aerodynamics force Aerodynamics force Full-dimensional state observer Full-dimensional state observer Thermal environment Thermal environment FG-CNTR cantilever plate FG-CNTR cantilever plate Vibration reduction Vibration reduction
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| GB/T 7714 | Lu, S. F. , Li, H. J. , Zhang, W. et al. Vibration reduction of FG-CNTR piezoelectric laminated composite cantilever plate under aerodynamic load using full-dimensional state observer [J]. | ENGINEERING STRUCTURES , 2022 , 255 . |
| MLA | Lu, S. F. et al. "Vibration reduction of FG-CNTR piezoelectric laminated composite cantilever plate under aerodynamic load using full-dimensional state observer" . | ENGINEERING STRUCTURES 255 (2022) . |
| APA | Lu, S. F. , Li, H. J. , Zhang, W. , Song, X. J. . Vibration reduction of FG-CNTR piezoelectric laminated composite cantilever plate under aerodynamic load using full-dimensional state observer . | ENGINEERING STRUCTURES , 2022 , 255 . |
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Abstract ：
In this paper, the nonlinear and dual-parameter chaotic vibrations are investigated for the blisk structure with the lumped parameter model under combined the aerodynamic force and varying rotating speed. The varying rotating speed and aerodynamic force are, respectively, simplified to the parametric and external excitations. The nonlinear governing equations of motion for the rotating blisk are established by using Hamilton's principle. The free vibration and mode localization phenomena are studied for the tuning and mistuning blisks. Due to the mistuning, the periodic characteristics of the blisk structure are destroyed and uniform distribution of the energy is broken. It is found that there is a positive correlation between the mistuning variable and mode localization factor to exhibit the large vibration of the blisk in a certain region. The method of multiple scales is applied to derive four-dimensional averaged equations of the blisk under 1:1 internal and principal parametric resonances. The amplitude-frequency response curves of the blisk are studied, which illustrate the influence of different parameters on the bandwidth and vibration amplitudes of the blisk. Lyapunov exponent, bifurcation diagrams, phase portraits, waveforms and Poincare maps are depicted. The dual-parameter Lyapunov exponents and bifurcation diagrams of the blisk reveal the paths leading to the chaos. The influences of different parameters on the bifurcation and chaotic vibrations are analyzed. The numerical results demonstrate that the parametric and external excitations, rotating speed and damping determine the occurrence of the chaotic vibrations and paths leading to the chaotic vibrations in the blisk.
Keyword ：
Blisk structure Blisk structure Lumped parameter model Lumped parameter model Dual-parameter chaotic vibrations Dual-parameter chaotic vibrations Amplitude-frequency response curves Amplitude-frequency response curves Parametric and external excitations Parametric and external excitations
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| GB/T 7714 | Zhang, W. , Ma, L. , Zhang, Y. F. et al. Nonlinear and dual-parameter chaotic vibrations of lumped parameter model in blisk under combined aerodynamic force and varying rotating speed [J]. | NONLINEAR DYNAMICS , 2022 , 108 (2) : 1217-1246 . |
| MLA | Zhang, W. et al. "Nonlinear and dual-parameter chaotic vibrations of lumped parameter model in blisk under combined aerodynamic force and varying rotating speed" . | NONLINEAR DYNAMICS 108 . 2 (2022) : 1217-1246 . |
| APA | Zhang, W. , Ma, L. , Zhang, Y. F. , Behdinan, K. . Nonlinear and dual-parameter chaotic vibrations of lumped parameter model in blisk under combined aerodynamic force and varying rotating speed . | NONLINEAR DYNAMICS , 2022 , 108 (2) , 1217-1246 . |
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Abstract ：
The applications of the new graphene platelet reinforced functionally graded (GPR-FG) composite materials are helpful to improve the overall performance of the rotating blade. However, the new GPR-FG rotating composite blade may produce the strong nonlinear vibrations under the coupling effects of the aerodynamic force and disturbed speed, which are one of the main reasons leading to the overall failure of the rotating blade. Therefore, it is of great value to analyze the nonlinear dynamics of the GPR-FG rotating composite blade under the aerodynamic force and varying speed. Based on the nonlinear dynamic model of the GPR-FG rotating composite blade, the resonant responses, global bifurcations and double-parameter multi-pulse chaotic vibrations of the rotating composite blade are studied for the first time. The prediction-correction continuation algorithm is used to obtain the amplitude-frequency response curves and force-amplitude curves of the GPR-FG rotating composite blade. It is found that there are the sudden changes in the resonant responses and complex nonlinear vibrations in the GPR-FG rotating composite blade. The extended Melnikov method is applied to study the global bifurcations and double-parameter multi-pulse chaotic vibrations of the GPR-FG rotating composite blade under the coupling excitations of aerodynamic force and disturbed speed. Through theoretical analysis and numerical simulation, we find that there are the complex double-parameter multi-pulse chaotic vibrations of the GPR-FG rotating composite blade. These results have the theoretical significance for the safe operation of the new GPR-FG rotating composite blade. (c) 2022 Elsevier Ltd. All rights reserved.
Keyword ：
Global bifurcations Global bifurcations Double-parameter nonlinear dynamics Double-parameter nonlinear dynamics Graphene platelet reinforced (GPR-FG) Graphene platelet reinforced (GPR-FG) rotating composite blade rotating composite blade Melnikov method Melnikov method Nonlinear resonant responsesExtended Nonlinear resonant responsesExtended
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| GB/T 7714 | Zheng, Y. , Zhang, W. , Liu, T. et al. Resonant responses and double-parameter multi-pulse chaotic vibrations of graphene platelets reinforced functionally graded rotating composite blade [J]. | CHAOS SOLITONS & FRACTALS , 2022 , 156 . |
| MLA | Zheng, Y. et al. "Resonant responses and double-parameter multi-pulse chaotic vibrations of graphene platelets reinforced functionally graded rotating composite blade" . | CHAOS SOLITONS & FRACTALS 156 (2022) . |
| APA | Zheng, Y. , Zhang, W. , Liu, T. , Zhang, Y. F. . Resonant responses and double-parameter multi-pulse chaotic vibrations of graphene platelets reinforced functionally graded rotating composite blade . | CHAOS SOLITONS & FRACTALS , 2022 , 156 . |
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Abstract ：
The stability and vibration of the telescopic wing are studied by the theoretical, numerical and experimental methods when the wing is in the deployment and retraction. The telescopic wing is simplified to a telescopic cantilevered laminated composite rectangular plate subjected to the first-order aerodynamic force and in-plane excitation. The time-varying dynamic characteristics of the telescopic cantilevered laminated composite rectangular plate are investigated by using the analytical, numerical and experimental methods. The approximate analytical solution of the nonlinear time-varying system is obtained by using the improved averaging method. Compared with numerical simulations, the approximate analytical results demonstrate a good agreement. The stability of the telescopic cantilever plate during the deploying process is studied by using the eigenvalue method, which demonstrates the effect of the velocity, acceleration and thickness on the stability of the deployment. The experimental results are consistent with the theoretical results and provide the theoretical basis and technical support for the axial moving wing.
Keyword ：
Averaging method Averaging method Experimental research Experimental research Time-varying dynamic characteristic Time-varying dynamic characteristic Telescopic wing Telescopic wing
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| GB/T 7714 | Zhang, W. , Gao, Y. H. , Lu, S. F. . Theoretical, Numerical and Experimental Researches on Time-Varying Dynamics of Telescopic Wing [J]. | JOURNAL OF SOUND AND VIBRATION , 2022 , 522 . |
| MLA | Zhang, W. et al. "Theoretical, Numerical and Experimental Researches on Time-Varying Dynamics of Telescopic Wing" . | JOURNAL OF SOUND AND VIBRATION 522 (2022) . |
| APA | Zhang, W. , Gao, Y. H. , Lu, S. F. . Theoretical, Numerical and Experimental Researches on Time-Varying Dynamics of Telescopic Wing . | JOURNAL OF SOUND AND VIBRATION , 2022 , 522 . |
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Abstract ：
This paper investigates the aeroelastic flutter and vibration reduction of functionally graded (FG) multilayer graphene nanoplatelets (GPLs) reinforced composite plates with piezoelectric patch subjected to supersonic flow. Activated by the control voltage, the piezoelectric patch can generate the active mass and active stiffness that can accordingly increase the base plate's stiffness and mass. As a result, it changes the GPLs reinforced plate's dynamic characteristics. The motion equation of the plate-piezoelectric system is derived through the Hamilton principle. Based on the modified Halpin-Tsai model, the effects of graphene nanoplatelets weight fraction and distribution pattern on the dynamic behaviors of the plate are numerically studied in detail. The result illustrates that adding a few amounts of grapheme nanoplatelets can effectually enhance the aeroelastic properties of the plates. Two kinds of control strategies, including the displacement and acceleration feedback control, are applied to suppress the occurrence of the flutter of the plate. It shows that the displacement and acceleration feedback control can improve the critical flutter Mach number of the plate by attaching active stiffness and active mass, respectively. Furthermore, the combined displacement and acceleration feedback control has a better control effect than that of considering only one of them.
Keyword ：
aeroelastic flutter aeroelastic flutter feedback control feedback control piezoelectric material piezoelectric material graphene nanoplatelets graphene nanoplatelets
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| GB/T 7714 | Chen, Jie , Han, Ruofan , Liu, Dekun et al. Active Flutter Suppression and Aeroelastic Response of Functionally Graded Multilayer Graphene Nanoplatelet Reinforced Plates with Piezoelectric Patch [J]. | APPLIED SCIENCES-BASEL , 2022 , 12 (3) . |
| MLA | Chen, Jie et al. "Active Flutter Suppression and Aeroelastic Response of Functionally Graded Multilayer Graphene Nanoplatelet Reinforced Plates with Piezoelectric Patch" . | APPLIED SCIENCES-BASEL 12 . 3 (2022) . |
| APA | Chen, Jie , Han, Ruofan , Liu, Dekun , Zhang, Wei . Active Flutter Suppression and Aeroelastic Response of Functionally Graded Multilayer Graphene Nanoplatelet Reinforced Plates with Piezoelectric Patch . | APPLIED SCIENCES-BASEL , 2022 , 12 (3) . |
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