An efficient higher order non-polynomial Quasi 3-D theory for dynamic responses of laminated composite plates

Adhikari, Balakrishna; Singh, B.N.

doi:10.1016/j.compstruct.2017.10.044

Cited by 40 publications

(4 citation statements)

References 44 publications

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“…For r = 2, the negative phase has the greater impact than the positive part as explained in Adhikari and Singh. 42 Thus, the laminate is experiencing the higher negative amplitude for r = 2 and minimum for r = 1. Also, it can be observed that the free vibration amplitudes is greatly affected by the duration of time for which the strong blast has the impact on laminate as manifested in Figure 11.…”

Section: Resultsmentioning

confidence: 98%

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Geometrically nonlinear static and dynamic analysis of CNT reinforced laminated composite plates: A finite element study

Adhikari

Singh

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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In this paper, a finite element study is conducted using the Green Lagrange strain field based on vonKarman assumptions for the geometric nonlinear static and dynamic response of the laminated functionally graded CNT reinforced (FG-CNTRC) composite plate. The governing equations for determining the nonlinear static and dynamic behavior of the FG-CNTRC plate are derived using the Lagrange equation of motion based on Reddy's higher order theory. Using the direct iteration technique, the nonlinear eigenvalues for analyzing the free vibration response are obtained and the nonlinear dynamic responses of the FG-CNTRC plate are encapsulated based on the nonlinear Newmark integration scheme. The impact of the amplitude of vibration on mode switching phenomena and the consequence of the duration of the pulse on the free vibration regime of the plate are outlined. Also, the effect of time dependent loads is studied on the normal stresses of the plate. Furthermore, the impact on the nonlinear static and dynamic response of the laminated FG-CNTRC plate of various parameters such as span-thickness ratio (b/h ratio), aspect ratio (a/b ratio), different edge constraints, CNT fiber gradation, etc. are also studied.

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Section: Resultsmentioning

confidence: 98%

“…Further, the nonlinear transient response of the laminate is not as smooth as linear in free vibration regime. 42 Thus, the consideration of the effect of nonlinearity is highly necessary for encapsulating the dynamic response of the laminate accurately.…”

Section: Resultsmentioning

confidence: 99%

Geometrically nonlinear static and dynamic analysis of CNT reinforced laminated composite plates: A finite element study

Adhikari

Singh

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…Adhikari and Singh [313] employed the HNP Quasi-3D approach for investigating the dynamic behavior of LCPs and the Lagrange equation has been used to determine the GEs, although the forced responses were obtained by implementing the NTI approach. It has been revealed that the dynamic behavior critically affected by the temperature variation in which, a reduction in NF has been noticed due to considering the temperature effect.…”

Section: Analytical Solution Without Considering the Sdementioning

confidence: 99%

Computational Linear and Nonlinear Free Vibration Analyses of Micro/Nanoscale Composite Plate-Type Structures With/Without Considering Size Dependency Effect: A Comprehensive Review

Al Mahmoud,

Safaei,

Sahmani

et al. 2024

Arch Computat Methods Eng

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Recently, the mechanical performance of various mechanical, electrical, and civil structures, including static and dynamic analysis, has been widely studied. Due to the neuroma's advanced technology in various engineering fields and applications, developing small-size structures has become highly demanded for several structural geometries. One of the most important is the nano/micro-plate structure. However, the essential nature of highly lightweight material with extraordinary mechanical, electrical, physical, and material characterizations makes researchers more interested in developing composite/laminated-composite-plate structures. To comprehend the dynamical behavior, precisely the linear/nonlinear-free vibrational responses, and to represent the enhancement of several parameters such as nonlocal, geometry, boundary condition parameters, etc., on the free vibrational performance at nano/micro scale size, it is revealed that to employ all various parameters into various mathematical equations and to solve the defined governing equations by analytical, numerical, high order, and mixed solutions. Thus, the presented literature review is considered the first work focused on investigating the linear/nonlinear free vibrational behavior of plates on a small scale and the impact of various parameters on both dimensional/dimensionless natural/fundamental frequency and Eigen-value. The literature is classified based on solution type and with/without considering the size dependency effect. As a key finding, most research in the literature implemented analytical or numerical solutions. The drawback of classical plate theory can be overcome by utilizing and developing the elasticity theories. The nonlocality, weight fraction of porosity, or the reinforcements, and its distribution type of elastic foundation significantly influence the frequencies.

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“…e spacecraft system is a typical constrained rigid-flexible coupling multibody system. In addition, these solar arrays are commonly composed of laminated shells involving fiber-reinforced composite materials, due to its high reliability, superior mechanical properties, high stiffnessto-weight ratio, and low fabrication cost [5][6][7]. e deployment of the composite laminated solar array exhibits a strong nonlinearity coupling between the large-rotation and largedeformation motions.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

et al. 2020

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Modern spacecraft are often equipped with large-scale, complex, and lightweight solar arrays whose deployment involves a highly dynamic movement. This paper proposed a novel adaptive proportional-derivative typed fuzzy logic control scheme for the attitude stabilization of a flexible spacecraft during the deployment of a composite laminated solar array. First, a constrained rigid-flexible coupling spacecraft model consisting of a rigid main body and a flexible solar array was proposed. The solar array, which is composed of composite laminated shells, was described by the absolute nodal coordinate formulation. Then, the detailed derivation of the adaptive fuzzy PD controller for attitude stabilization of the spacecraft was discussed. In addition, the spacecraft dynamic model which integrated the adaptive fuzzy PD controller was derived as a set of differential-algebraic equations. Several simulations were developed to investigate the solar array deployment dynamics and to verify the effectiveness of the proposed adaptive fuzzy PD controller. The results suggested that the proposed dynamic model is able to exactly describe the deployment dynamics of the composite laminated solar array. The solar array deployment causes obvious translational and rotational motions of the spacecraft. The proposed adaptive fuzzy PD control scheme has better performance in terms of the control precision and time response in stabilizing spacecraft during the deployment of the composite laminated solar array, comparing with that of the conventional PD controller.

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An efficient higher order non-polynomial Quasi 3-D theory for dynamic responses of laminated composite plates

Cited by 40 publications

References 44 publications

Geometrically nonlinear static and dynamic analysis of CNT reinforced laminated composite plates: A finite element study

Geometrically nonlinear static and dynamic analysis of CNT reinforced laminated composite plates: A finite element study

Computational Linear and Nonlinear Free Vibration Analyses of Micro/Nanoscale Composite Plate-Type Structures With/Without Considering Size Dependency Effect: A Comprehensive Review

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

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