Qualification: 
Ph.D
Email: 
v_sivakumar@cb.amrita.edu

Dr. Sivakumar V. received his Ph. D. in Solid Mechanics from IIT Madras in 2006. At IIT, he carried out a project sponsored by the Vikram Sarabhai Space Center (VSSC) of the Indian Space Research Organization (ISRO) on rocket casing stress analysis under the guidance of Prof. R. Palaninathan. 

Prior to pursuing his Ph. D., Dr. Sivakumar worked in at the FE software development companies, Altair Engineering and EASi Technologies in Bangalore in various capacities. He received his Master's degree in Structural Engineering and was involved in research at the Aeronautical Development Agency (ADA) Bangalore on the development of capacitance-based accelerometers with Dr. A. R. Upadhya. The project was sponsored by the IT firm SSPL.    

Dr. Sivakumar joined Amrita in 2006. He is currently co-investigator in an ISRO project on the analysis of multi-layer shear damper. In the course of his career, he has done numerous structural analyses in various fields such as framed structures, automotive bodies and aerospace structures. 

His areas of interests are Non-Linear Structural Mechanics, Composite Mechanics and Bucking Analysis with Real Imperfections. He has had exposure to most FE codes, including ABAQUS, NASTRAN, LS-DYNA, ANSYS and HYPERWORKS.

Publications

Publication Type: Journal Article

Year of Publication Publication Type Title

2017

Journal Article

T. R. S. Kumar, Dr. Sivakumar V., Dr. Balajee Ramakrishnananda, Arjhun, A. K., and , “Numerical investigation of two element camber morphing airfoil in low reynolds number flows”, Journal of Engineering Science and Technology, vol. 12, pp. 1939-1955, 2017.[Abstract]


Aerodynamic performance of a two-element camber morphing airfoil was investigated at low Reynolds number using the transient SST model in ANSYS FLUENT 14.0 and eN method in XFLR5. The two-element camber morphing concept was employed to morph the baseline airfoil into another airfoil by altering the orientation of mean-line at 35% of the chord to achieve better aerodynamic efficiency. NACA 0012 was selected as baseline airfoil. NACA 23012 was chosen as the test case as it has the camber-line similar to that of the morphed airfoil and as it has the same thickness as that of the baseline airfoil. The simulations were carried out at chord based Reynolds numbers of 2.5×105 and 3.9×105. The aerodynamic force coefficients, aerodynamic efficiency and the location of the transition point of laminar separation bubble over these airfoils were studied for various angles of attack. It was found that the aerodynamic efficiency of the morphed airfoil was 12% higher than that of the target airfoil at 4° angle of attack for Reynolds number of 3.9×105 and 54% rise in aerodynamic performance was noted as Reynolds number was varied from 2.5×105 to 3.9×105. The morphed airfoil exhibited the nature of low Reynolds number airfoil. © School of Engineering, Taylor’s University.

More »»

2015

Journal Article

V. A. Chakkaravarthy, Krishnan, N., Nivetha, M., Vinu, R., and Dr. Sivakumar V., “Strength prediction of composite T-joints with and without cut-outs”, International Journal of Applied Engineering Research, vol. 10, pp. 35825-35831, 2015.[Abstract]


Composite materials are widely used in the aircraft industry. The spars and ribs in aircraft wings attached to the skin form a T-joint. The objective of this project is to analyse the differences in the structural properties of composite T-joints with and without cut-outs, and thus optimize a cut-out configuration that gives the best structural properties. A composite T-joint was modelled with standard dimensions using T-300/Carbon epoxy Prepreg as the material. The model was subjected to pulling, shear and bending loads. Finite element analysis and Tsai-Hill failure analysis were done on the model. Maintaining a constant area, different cut-out configurations were modelled on the T-joint and analysed just as the model without cut-out. The results obtained for all the models were tabulated, and the structural integrity of the models was compared using the Tsai-Hill failure criteria. The best cut-out configuration was identified based on the results obtained. © Research India Publications.

More »»

2015

Journal Article

Dr. Sivakumar V., Kumar, G. B., and Gautham, A., “Crack Initiation Study on Aircraft Composite Rib with Semi-elliptical Surface Flaw”, Journal of Failure Analysis and Prevention, 2015.[Abstract]


A parametric study on crack initiation was done by having different sizes of cracks at different locations in a rib section of an aircraft using finite element techniques. A semi-elliptical surface flaw in a typical Boeing-747 rib section having circular cut-out and experiencing an in-plane shear loading was considered for the analysis. A laminated composite square plate around a centrally located cut-out was selected in the wing rib for computation purpose. A delamination has been modeled in between the composite layers in the form of a semi-elliptical surface crack using node duplication technique. As there are no theoretical solutions for mixed mode loading problems, the general purpose finite element package ABAQUS was used to obtain the Stress Intensity Factor (SIF) along the crack edge. These stress intensity factor (KC) values were further compared with the fracture toughness of the material to determine the probability of crack initiation. It was observed that the modes of failure change with the dimensions of the crack and also showed a greater tendency towards the crack initiation. © 2015 ASM International

More »»

2012

Journal Article

Dr. Sivakumar V., Arjun, R. K., Ishwarya, V., Nithya, S., Sunder, S., and Thilak, B. N., “Optimization of cut-out shape on composite plate under in-plane shear loading”, Journal of Failure Analysis and Prevention, vol. 12, pp. 204-213, 2012.[Abstract]


The wing in flight condition is subjected to heavy aerodynamic loads that in turn lead to a shear flow over the wing ribs that support it. Cut-outs change the mechanical behavior of plates, as they redistribute the stresses and are influenced by the shape of the cut-out. A three-dimensional displacement-based finite element analysis is performed to study the symmetric, laminated composite plate of 20 layers. The analysis is performed to obtain the in-plane and out of plane performances of the laminate. Five basic cut-out geometries, viz., circle, square, diamond, ellipse with major axis along the y-axis, and another ellipse with major axis along the x axis were used for the numerical analysis. A cut-out geometry is generated based on the results of analyses performed on five basic geometries to optimize the performance. The optimized cut-out is associated with the least Tsai-Hill and Hashin failure index as compared with the five basic geometries. © ASM International 2012.

More »»

Publication Type: Conference Paper

Year of Publication Publication Type Title

2012

Conference Paper

P. Sudheesh, Jayakumar, A., Siddharth, R., Srikanth, M. S., Bhaskar, N. H., Dr. Sivakumar V., and Sudhakar, C. K., “Cyclic prefix assisted sparse channel estimation for OFDM systems”, in 2012 International Conference on Computing, Communication and Applications, Dindigul, Tamilnadu, 2012.[Abstract]


In this paper an efficient algorithm is presented for the estimation of a channel modelled as sparse for an OFDM system. Conventional Pilot-Based techniques and blind estimation techniques require a large number of pilot tones and complex mathematical computations respectively to estimate the channel vector. This drawback is particularly pronounced in sparse systems where the effective channel vector has a very few number of taps. The proposed method uses a modification made to the Cyclic Prefix to detect the position of the most significant taps (MST) for a sparse channel. Least Square estimation method is then used to effectively estimate the channel vector. Prior knowledge of the most significant tap positions obtained from the cyclic prefix ensures spectral and computational efficiencies. More »»

207
PROGRAMS
OFFERED
5
AMRITA
CAMPUSES
15
CONSTITUENT
SCHOOLS
A
GRADE BY
NAAC, MHRD
8th
RANK(INDIA):
NIRF 2018
150+
INTERNATIONAL
PARTNERS