Hukum Chand Dewangan
@nitrkl.ac.in
Research Scholar (Ph.D.)
National Institute of Technology, Rourkela
RESEARCH INTERESTS
Mechanics of Composite Materials, Functionally Graded Materials, Metal Matrix Composites, Damage Modelling, Finite Element Method, Geometrical Nonlinear Analysis
Scopus Publications
Scholar Citations
Scholar h-index
Scholar i10-index
Scopus Publications
Prashik Malhari Ramteke, Erukala Kalyan Kumar, Hukum Chand Dewangan, B. K. Patle, and Subrata Kumar Panda
Springer Science and Business Media LLC
Erukala Kalyan Kumar, Vikash Kumar, Nitin Sharma, Hukum Chand Dewangan, Ashish Kumar Meher, and Subrata Kumar Panda
Springer Science and Business Media LLC
Rishabh Pal, Mrinal Chaudhury, Hukum Chand Dewangan, Chetan Kumar Hirwani, Vikash Kumar, and Subrata Kumar Panda
Springer Science and Business Media LLC
Rajesh Kumar Satankar, Nitin Sharma, Pankaj V. Katariya, Vikash Kumar, Hukum Chand Dewangan, Ankit Pal, and Subrata Kumar Panda
Elsevier BV
Hukum Chand Dewangan, Subrata Kumar Panda, Nitin Sharma, Samy Refahy Mahmoud, Dineshkumar Harursampath, and Vinyas Mahesh
Elsevier BV
Hukum Chand Dewangan, Subrata Kumar Panda, and Nitin Sharma
Elsevier BV
Vikash Kumar, Erukala Kalyan Kumar, Hukum Chand Dewangan, Nitin Sharma, Subrata Kumar Panda, and S. R. Mahmoud
Springer Science and Business Media LLC
Hukum Chand Dewangan, Subrata Kumar Panda, Samy Refahy Mahmoud, Dineshkumar Harursampath, Vinyas Mahesh, and Mohammed Balubaid
Springer Science and Business Media LLC
Hukum Chand Dewangan and Subrata Kumar Panda
ASME International
Abstract The cutout and temperature loading influences on the nonlinear frequencies of the laminated shell structures are predicted numerically using two different types of geometrical nonlinear strain-displacement relationships to count the large deformation. The displacement of any generic point on the structural panel is derived using the third-order shear deformation theory (TSDT). Moreover, the direct iterative method has been adopted to obtain the nonlinear eigenvalues in conjunction with the isoparametric finite element (FE) steps. The present analysis includes the effect of temperature and the temperature-dependent composite elastic properties on the thermoelastic frequencies. This study intends to establish the Green-Lagrange type of nonlinear strain's efficacy in computing the nonlinear frequency of layered structure with and without cutout instead of von-Karman strain kinematics. The numerical model's validity has been established by comparing the results to previously published results. In addition, experimentally obtained fundamental frequency values of a few modes are compared to numerical proposed numerical results under the thermal loading. Finally, the effects of cutout (shape and size) and the associated structural geometrical parameters on the nonlinear thermal frequency responses of the laminated structure are expressed in the final output form.
Vikash Kumar, Hukum Chand Dewangan, Nitin Sharma, Subrata Kumar Panda, and S. R. Mahmoud
Springer Science and Business Media LLC
Vikash Kumar, Hukum Chand Dewangan, Nitin Sharma, and Subrata Kumar Panda
Springer Science and Business Media LLC
Kalyan Kumar Erukala, Pradeep Kumar Mishra, Hukum Chand Dewangan, Subrata Kumar Panda, and Madhuresh Dwivedi
Springer Science and Business Media LLC
Hukum Chand Dewangan and Subrata Kumar Panda
American Society of Civil Engineers (ASCE)
Vikash Kumar, Hukum Chand Dewangan, Nitin Sharma, and Subrata Kumar Panda
Elsevier BV
Hukum Chand Dewangan, Nitin Sharma, and Subrata Kumar Panda
SAGE Publications
The influences of cut-out on the static and dynamic deflection of the multilayered composites under thermomechanical are predicted numerically. In this regard, a mathematical model is prepared using the third-order kinematics associated with the isoparametric finite element steps. Moreover, the solution accuracy of the derived model has been tested frequently by solving a series of examples (obtained from MATLAB code) similar to the published one. In addition, the model verification is extended further by comparing the numerical results with the in-house experimental data recorded under the static and dynamic loading conditions. The equivalent single-layer theoretical model (prepared for the cut-out abided laminated structure) exactness is maintained by considering the variation of in-plane displacement as cubic. In contrast, the state space variable along with the thickness is constant. Additionally, the experimental comparisons are made considering the influences of different cut-out geometry, temperature increment, and loading intensities. The effects of cut-out and the laminated structural geometrical parameters that affect the final design consideration due to the thermomechanical loading as well as the temperature-dependent properties are computed using the derived model, and the outcomes are discussed in detail.
Pruthwiraj Sahu, Nitin Sharma, Hukum Chand Dewangan, and Subrata Kumar Panda
World Scientific Pub Co Pte Ltd
Thermal frequency responses of the hybrid laminated composite panel are theoretically computed using the finite element model and for the first time compared with in-house experimental data. The structural model for hybrid panel is derived using higher-order displacement polynomial functions (to maintain the necessary stress/strain continuity) and discretized through the isoparametric finite elements. Moreover, the elastic properties of the composite are evaluated suitably including thermal and physical parameters of the advanced fibers (Glass/Carbon/Kevlar) with the help of experimentations and numerical tool (via ABAQUS using mean-field homogenization). The variation of modal responses due to the change in temperature increment is computed through a generic computer code generated via the higher-order mathematical model. The numerical frequency values are compared with the earlier published numerical results and the experimentally recorded eigen frequencies. The experimental verifications related to the end boundaries indicate that the incorporation of the clamped boundary for one edge doubles the frequency, whereas the fraction of Kevlar fiber does not influence the stiffness (due to longitudinal modulus) parameter irrespective of the temperature change. Further, the conclusive understandings of the hybrid composite structural panel due to the inclusion of different advanced fibers and other design parameters (geometry, boundary and temperature) are deliberated in detail.
Hukum Chand Dewangan and Subrata Kumar Panda
Springer Science and Business Media LLC
The vibrational responses are predicted numerically for the layered shell panel structure with and without cutout under the variable temperature loading and corrugated composite properties. The presence of variable cutout shapes (circular/elliptical/square and rectangular) and sizes are modelled via a generic mathematical macro-mechanical model in the framework of the cubic-order kinematic model. Also, the present model includes the variation of composite properties due to the change in environmental conditions, i.e. the temperature-dependent (TD) and -independent (TID) cases. The computational responses are obtained by taking advantages of the isoparametric finite element technique and the Hamilton principle to derive the final governing equation. The total Lagrangian approach is adopted to compute the responses using the specialized computer code prepared in the MATLAB platform. The frequency responses are predicted considering the effect of a cutout, including the environmental variation and compared with previously published eigenvalues. The model versatility is tested over a variety of examples considering the shell configurations (plate, cylindrical, spherical, hyperboloid, and elliptical), the influential cutout parameter (shape, size, and position) and temperature loading including the corrugated composite properties.
Vikash Kumar, Hukum Chand Dewangan, Nitin Sharma, and Subrata Kumar Panda
Elsevier BV
Hukum Chand Dewangan, Nitin Sharma, and Subrata Kumar Panda
American Institute of Aeronautics and Astronautics (AIAA)
The influence of two different types of nonlinear strain-displacement kinematics (Green–Lagrange and von Karman) and their importance are investigated in this analysis by computing the static defle...
Hukum Chand Dewangan, Subrata Kumar Panda, Nitin Sharma, and Chetan Kumar Hirwani
CRC Press
Chetan Kumar Hirwani, Sandeep Tiwari, Pradeep Kumar Mishra, Hukum Chand Dewangan, and Subrata Kumar Panda
Informa UK Limited
Subham Mohapatra, Nitin Sharma, Hukum Chand Dewangan, and Subrata Kumar Panda
Informa UK Limited
Pruthwiraj Sahu, Nitin Sharma, Hukum Chand Dewangan, and Subrata Kumar Panda
World Scientific Pub Co Pte Ltd
The time-dependent deflection values of the flat/curved hybrid fibre (Glass–Carbon–Kevlar)-reinforced composite panels under the influence of the mechanical loading (UDL and SDL) and the elevated thermal environment are analyzed in this research. To compute the numerical responses, a higher-order kinematic model is prepared considering the effect of single/double curvature of the shell panel. The weak form of the governing equation is established through the variational technique. The steady-state deflections are obtained by solving the discrete form of governing equation of transient vibrations using finite element method (FEM) by employing Newmark’s time integration method in MATLAB environment. The isoparametric Lagrangian element (nine-noded) is adopted to discretize the system equation of the hybrid panels. The validity of the numerical solutions, computed using the experimental hybrid composite properties, is verified with the experimental (in-house) results as well as with the benchmark results available in the published literature. Finally, the parametric study of dynamic deflection characteristics of hybrid composite shallow shell panels is carried out by varying the parameters such as curvature ratio, support conditions, hybrid schemes and type of loading in the elevated thermal environment and the results are discussed in detail.
Hukum Chand Dewangan, Nitin Sharma, Mukesh Thakur, Subrata Kumar Panda, and Pruthwiraj Sahu
Springer Science and Business Media LLC
The layered structural deflection responses are predicted numerically in this research considering the combined influence of different external and environmental loading (thermal and mechanical), including the variable elastic strength due to the hybridization of varying fibre (glass/carbon/Kevlar). In addition, the analysis includes the effect of panel curvature parameters to define different geometrical shapes. The numerical model of the layered structure is derived mathematically via the polynomial type of kinematic model in association with isoparametric formulation (using the finite element steps). The layered structure is modelled based on the assumption of equivalent single-layer theory. The predicted deflections of layered structures are verified with experimental data, including the very own observed properties. Additionally, the necessary elevated thermal environment is designed to perform the required bending test. The current numerical results are obtained through a well-designed computer code prepared using the proposed mathematical model. The finite element deflection values are obtained through the MATLAB code and compared with the experimental test result by simulating identical physical conditions adopted during the experimental test. The higher-order finite element model is being utilized for numerical experimentations considering variable input data. The results obtained for one/many variable input parameters and the corresponding output are discussed in different aspects. The outcome of this research is a complete and generic-type computational solution for the laminated structure considering the effect of curvature, elevated thermal environment and hybridization.
Hukum Chand Dewangan, Mukesh Thakur, S.S.K. Deepak, and Subrata Kumar Panda
Elsevier BV
Abstract This is the first time two different geometrical nonlinear strain–displacement relationships are adopted to model the laminated shell structure with the cutout to predict the eigenvalues considering a higher-order displacement model. The nonlinear solution for the natural frequency value is obtained using Picard's iterative method in association with the isoparametric finite element method . The present research mainly indicates the inevitability of Green-Lagrange's nonlinear strain in the framework of higher-order displacement kinematics instead of von-Karman's nonlinear strain including all of the nonlinear higher-order strain. The predicted nonlinear solution consistency is verified by solving a series of examples, as same as the source data. The influences of the cutout (shape and size) related data and the corresponding geometrical parameters of the multilayered structure are expressed in the final output form. Lastly, the inclusive inferences are highlighted to recommend the nonlinear model to analyze a flexible laminated structural component with and without cutout.