Geometrically Nonlinear Transient Response of Laminated Plates with Nonlinear Elastic Restraints

Yang, S.W.; Yang, Qing-Sheng

doi:10.1155/2017/2189420

Cited by 8 publications

(5 citation statements)

References 37 publications

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“…The calculated results are reliable and efficient, which can solve the free vibration and forced vibration of composite laminates. Yang and Yang [27] analyzed the dynamics of laminated plates under nonlinear elastic constraints, established different binding models, and obtained the transverse displacement of laminated plates through transient analysis. Using the analysis principle of micromechanics, Nallim et al [28] proposed a variational formula for the analysis of the free vibration of the elastic constraint asymmetric composite laminates and gave the influence of different mechanical and geometric parameters on the dynamic properties of different laminates.…”

Section: Introductionmentioning

confidence: 99%

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Wang

Ren

et al. 2021

International Journal of Aerospace Engineering

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In this paper, in order to understand the influence of the unbalanced coefficient of composite laminates on the static aeroelasticity of high aspect wings, a series of numerical simulation calculations were carried out, and this work wants to provide some reference for the structural design of aircraft. Considering the influence of geometric nonlinearity, the unidirectional fluid-solid coupling calculation method based on loose coupling is used to control the change of unbalanced coefficient of laminates on the basis of layering angle, layering thickness, and layering region, so as to observe the changes caused to the wings. The relationship between the unbalanced coefficient and the constant thickness layup and the variable thickness layup with 0° and ±45° layup angles was studied, respectively. Then, the layup angle of 90° was added to study the influence of the unbalanced coefficient on the static aeroelasticity of the wing structure with the change of the layup angle and the different choice of layup region. The results show that the deformation is the smallest when the unbalanced coefficient is 0.5, and the deformation trend is evenly distributed along both sides when the unbalanced coefficient is 0.5. When the unbalanced coefficient is changed, adding the 90° layup angle can significantly reduce the overall deformation of the wing and show different sensitivity characteristics to different layup areas. The increase of the unbalanced coefficient makes the chordal displacement gradually change from linear distribution to nonlinear distribution along the spread direction, and the displacement will gradually decrease.

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Section: Introductionmentioning

confidence: 99%

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Wang

Ren

et al. 2021

International Journal of Aerospace Engineering

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“…In order to fully comprehend the difficulties that come with non-linear modelling of structural joints considering micro-slip and macro-slip, it is essential to consider the repeatability and variability of jointed structures [13,14]. Nonlinear joint parameters are computed by use of harmonic probing and Volterra series [15], sub-structure synthesis theory [16], nonlinear discrete-time systems [17], and varied constraint force model where flexible pads which are modeled by rotational and translational springs [18].…”

Section: Introductionmentioning

confidence: 99%

Non-linear modeling and parameter identification of a bolted joint using substructure synthesis theory

Hussain,

Ingole

2024

Eng. Res. Express

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Engineering applications require accurate modeling and parameter identification to anticipate bolted joint behavior under different loading circumstances. Bolted joints are extensively used in civil and mechanical structures. In this research study, cubic stiffness non-linearity is examined and a comprehensive model, which can exhibit the non-linearity of joint behavior, is developed. This is achieved by modeling the bolted joint which is connected at one end of a cantilever beam. Mathematical model is established using concept of sub structure synthesis theory by considering non-linear translational stiffness and non-linear rotational stiffness as a boundary condition. Non-dimensional natural frequencies are estimated by assuming stiffness parameters and joint parameter estimation for translational spring having nonlinear stiffness is calculated using second order curve fitting technique. Furthermore, estimated and exact value of cubic stiffness coefficient are compared. The experimental results shows that the percentage error of estimation for all the modes are less than 8 %. The experimentally determined natural frequencies are further contrasted with an analytical results to validate a precision of generated model. Present work contributes in improving the bolted joint analysis by providing a solid non-linear modeling and parameter identification methodology. This methodology enhances design practices and ensures the durability of engineering structures and mechanical systems by improving bolted joint comprehension.

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“…Yang et al [12][13][14] established an equivalent dynamic model of the rotating shaft, and analyzed the in uence of the degree of misalignment, shaft diameter and shaft length on the vibration characteristics of the system under the action of coupling misalignment, rotor unbalance and their coupling faults.…”

Section: Introductionmentioning

confidence: 99%

Experiment and Simulation Analysis of the Vibration Response of the Rotor-bearing System

Qian¹,

Ran²,

Ding³

et al. 2023

Preprint

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The unbalanced mass of the rotor-bearing system may cause abnormal vibration of the rotor-bearing system, which may affect the safe operation of the system in severe cases. In this paper, the rotor-bearing system fault simulation test bench and MADYN 2000 were used to test and simulate the single-disk shafting rotor mass unbalance fault. The research analyzes the influence of speed, unbalanced mass, support stiffness, and phase of unbalanced mass on the vibration response of the rotor-bearing system. The results show that when the speed is higher than the first-order critical speed, after the rotor starts, the amplitude gradually increases with the speed, reaches the peak at the first-order critical speed, and then gradually decreases to a stable value. Due to the anisotropy of the bearing support, the rotor has different amplitudes in each direction, but the change trend is the same, the support stiffness is small, and the stable value is reached faster. When the rotation speed and the unbalanced mass phase are the same, the rotor amplitude and the rotor unbalanced mass have a linear relationship. When the speed and unbalanced mass are the same, the rotor amplitude fluctuates with the change of the loading phase, and the fluctuation period is π. The research results have certain reference significance for the fault diagnosis and dynamic characteristics analysis of the unbalanced response of the rotor-bearing system.

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Geometrically Nonlinear Transient Response of Laminated Plates with Nonlinear Elastic Restraints

Cited by 8 publications

References 37 publications

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Effects of Unbalanced Lamination Parameters on the Static Aeroelasticity of a High Aspect Ratio Wing

Non-linear modeling and parameter identification of a bolted joint using substructure synthesis theory

Experiment and Simulation Analysis of the Vibration Response of the Rotor-bearing System

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