Qualification: 
Ph.D
v_sivakumar@cb.amrita.edu
Phone: 
Cell: +91 94864 20028 | Landline: +91 422 2685000 [Ext: 5573]

Dr. V. Sivakumar is the Vice Chairman and Associate Professor at the Department of Aerospace Engineering at School of Engineering, Amrita Vishwa Vidyapeetham, Coimbatore since July 2006. Dr. Sivakumar received his Ph. D. in Applied 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, 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 under the guidance of Dr. A.R. Upadhya, former Director, CSIR National Aerospace Laboratories(NAL).

Dr. Sivakumar has published over 30 research article in polymeric composite, fracture mechanics and aerospace component design related to aviation, space and nuclear applications in international journals and conferences. Dr. Sivakumar reviewer of ASME Proceedings, Journal of Engineering Science and Technology and member of board of studies in various universities.

Dr. Sivakumar carried out many sponsored and research projects of ISRO, BARC and DRDO organizations. Dr. Sivakumar has life memberships in the Indian Society for Advancement of Materials and Processing Engineering (ISAMPE) and The Institution of Engineers (M.I.E) in India. Dr. Sivakumar’s major research interest includes Linear and Non-Linear Stress Analysis, Advanced Structural Design using Finite Element Methods, Analysis and Development of Composite Materials and Fracture Mechanics. Dr. Sivakumar exposure to most of FE codes, including ABAQUS, NASTRAN, LS-DYNA and HYPERWORKS.

Education

  • 2006 : Ph. D. in Applied Mechanics
    Indian Institute of Technology, Madras, Chennai
  • 1999 : M. E. in Structural Engineering
    Government College of Technology, Coimbatore
  • 1996 : B. E. in Civil Engineering
    Coimbatore Institute Technology, Coimbatore

Professional Appointments

Year Affiliation
January 2010 - Present Associate Professor, Department of Aerospace Engineering, School of Engineering, Amrita Vishwa Vidyapeetham, Coimbatore
June 2006 - December 2009 Assistant Professor, Department of Aerospace Engineering, School of Engineering, Amrita Vishwa Vidyapeetham, Coimbatore
January 2002 - June 2006 Research Scholar (HTRA), Indian Institute technology, Madras
March 2000 - December 2001 Team Leader, Altair Engineering, Bangalore
July 1999 - March 2000 Design Engineer, EASi Technologies, Bangalore
December 1996 - October 1997 Assistant Engineer, S&S Constructions, Coimbatore

Certificates, Awards, Honors and Societies

  • Life Member of Indian Engineers (M-1462215) in The Institution of Engineers (India), Kolkata, India.
  • Life Member (L-1451) in Indian Society for Advancement of Materials and Processing Engineering (ISAMPE), Bangalore, India.
  • Founder Life Member (FLM-SFA-0381) of Society for Failure Analysis, Hyderabad, India
  • Member, Board of studies, Aerospace Engineering Department, Amrita Vishwa Vidyapeetham, Coimbatore.
  • Member, Board of Studies, Aerospace Engineering Department, Karpagam University, Coimbatore.
  • Subject Expert, Board of Studies, Aeronautical Department, Sri Ramakrishna Engineering College, Coimbatore for the academic year 2019-20.
  • Subject Expert, Board of Studies , Civil Engineering Department, Government College of Technology (GCT), Coimbatore for the academic year 2019-20.
  • Subject Expert, Board of Studies, Aeronautical Department, Sri Ramakrishna Engineering College, Coimbatore for the academic year 2018-19.
  • Reviewer for ASME 2017 Gas Turbine (GT) India Conference conducted by ASME International GT Institute at Bangalore, India . December 07-08, 2017
  • Reviewer of Journal of Engineering Science and Technology,ISSN : 1823-4690.
  • Reviewer for ASME 2014 Gas Turbine (GT) India Conference conducted by ASME International GT Institute at New Delhi, India . December 15-17, 2014.
  • Reviewer for ASME 2013 Gas Turbine (GT) India Conference conducted by ASME International GT Institute and CSIR-National Aerospace Laboratories, Bangalore. December 5-6, 2013.
  • Member in question paper passing board in Anna University of Technology, Coimbatore October, 2011.
  • Doctoral committee member for Ph. D. candidates in P.S.G College, Dept. of Mechanical Engineering, Coimbatore, affiliated to Anna University.
  • Reviewer for National conference on energy efficient mechanical system design and manufacturing at PSG College of technology, Coimbatore. March 2011
  • Chaired in FLIEGEN 11- An Aviation Awareness Symposium at Park college of Engineering and technology, Coimbatore, February 2011.
  • Chaired in National conference on Advances in steel, concrete and composite structures (ASCCS09), Government College of technology, Coimbatore, India. April 2009.

Area of Specialization

  • Linear and Non-Linear Stress Analysis
  • Advanced Structural Design using Finite Element Methods
  • Analysis and Development of Composite Materials
  • Fracture Mechanics

Achievements/Prizes

  • The only recipient of EXCELLENT grade in Master of Engineering (M.E.) project.
  • Distinction and First rank holder in Bachelor of Engineering (B.E) Examinations
  • Prize winner for class First rank in S.S.L.C examination
Year Title Sponsor
2018 Development of Light Weight Bullet Proof Material (Co-Investigator) TDFS-DRDO, Govt. of India
2013 Investigation on effect of space radiations on space durable polymeric nano composite for future generation space missions.(Principal Investigator) Bhabha Atomic Research Center, Govt. of India
2013 Investigation on Carbon Nano Fiber Reinforced Polyether Ether Ketone/Polyether Imides as Polymer Composite Container for Long Time Nuclear Waste Disposal (Co- Investigator) Bhabha Atomic Research Center, Govt. of India
2009 Analysis and Evaluation of Multilayer Shear Damped Visco-Elastic Treatments for Launch Vehicle Application (Co-Investigator) ISRO, Govt. of India
2004 S200 Motor Case Structural Analysis for Handling and testing Conditions. (Resource Person) ISRO, Govt. of India
1999 FE Analysis and Design of a Capacitance-Type Miniature Accelerometer. (Resource Person) ADA-SSPL

Talk Delivered

Year Details
2019 "Mechanics of Composite Structures", expert lecture delivered in Nation seminar on Advancement in Materials Technology for Aerospace Application in Kumaraguru College of Technology, Coimbatore on 03rd May 2019.
2019 "Mechanics of Composite Structures Used in Aerospace Industries" , guest lecture delivered in the Department of Aeronautical Engineering, Sri Ramakrishna Engineering College, Vattamalaipalayam, Coimbatore on 16th March 2019.
2019 "Various Structural Beams Used in Commercial Aircrafts" , guest lecture delivered in the Department of Aeronautical Engineering, Sri Ramakrishna Engineering College, Vattamalaipalayam, Coimbatore on 28th February 2019.
2018 "Mechanics of Aircraft Structures", guest lecture delivered in the Department of Aeronautical Engineering, Karpagam University, Coimbatore on 25th September 2018.
2016 "Finite Element Modelling and Analysis of Composite Structures", guest lecture at TEQIP-II sponsored FDP on Finite Element Methods & Application at the PSG College of Technology, Coimbatore, 14th July 2016.
2016 "Mechanical Behaviour of Materials and General Requirements of Materials for Aerospace Applications", expert lecture in Two Day Short Term Course on Materials and Testing at the Karpagam Institute of Technology, Coimbatore, 12th February 2016.
2015 "Torsion on Plates", expert lecture in faculty development programme on "Aircraft Structures-II", jointly organised by Nehru Institute of Engineering and Technology and Anna University, Chennai, 26th May 2015.
2015 "FEM Applications in Aeronautics", a special lecture given in the Workshop on Finite Element Methods and its Applications at the Department of Mechanical Engineering, Anna University, Coimbatore, 13th March 2015.
2015 "Crack Initiation Study On Aircraft Composite Rib With Semi Elliptical Surface Flaw", keynote lecture given inthe National Conference on "Emerging Trends in Mechanical Sciences, NCETMS15" at the Karpagam University, Coimbatore on 27th February 2015
2014 "Composite Materials and Fracture Mechanics" in Faculty Development Program at Karpagam University Coimbatore on 20th June 2014.
2013 Mechanics of Hybrid Composites” in Two Days CSIR Sponsored National Level Seminar on mechanics, processing and characterization of high performance hybrid composite materials at KPR Institute of Engineering and Technology, Coimbatore on 24th August 2013.
2012 Mechanics of Laminated Composites” in Two Days Workshop on Composite Materials at KPR Institute of Engineering and Technology, Coimbatore on 25th August 2012.
2012 What We Do in Aerospace Department at the University” in All India Radio-Coimbatore, Educational Broadcast on 16th April 2012.
2011 Aero Structures” in the Department of Aeronautical Engineering, Karpagam University, Coimbatore, 28th September 2011.
2008 FE 3D Formulation and Case Studies”in Staff Development Programme on Finite Element Analysis at Dr. Mahalingam College of Engineering and Technology, Pollachi, June 2008.
2007 Principles of Solid Mechanics and Variational Calculus” in Short term training programme on Finite Element Technology for Reliable Product Development (FETREP’07) at Government College of technology, Coimbatore, May 2007.
2007 Thin Steel structures – Case Studies” in One Day Workshop on Steel in Construction – Today & Tomorrow at Govt. College of Technology, Coimbatore, February 2007.
2006 Use of FE Software in Structural Engineering” in Faculty Development Programme on Software Applications in Civil Engineering (SACE) at Govt. College of Technology, Coimbatore, December 2006.

Workshop and Training Programs Undergone

Year Details
2016 Five-day workshop on " Mechanics of Fracture" conducted by GIAN sponsored Indian Institute of technology - Madras at Chennai, 19 - 23 of December 2016.
2015 Three-day Workshop on "Aircraft Structural Testing" by Society of Indian Aerospace Technologies and Industries (SIATI) and IIAEM, Jain University at Bangalore, 10 -12 of December 2015.
2014 One Day seminar on “ Topics in Engineering Failure Analysis” organized by Amrita School of Engineering and Society for Failure Analysis at Amrita University, Coimbatore on 26th April 2014.
2011 One Day Seminar on Aero-Structures Design & Certification Conducted by Regional Centre for Military Airworthiness (Aircraft), CEMILAC, Bangalore, 25, August 2011
2010 Workshop on “High Impact Teaching Skills (MISSION 10X)” conducted by Dale Carnegie Training Institute and Wipro at Amrita Vishwa Vidyapeetham University, Coimbatore, 20 – 21 Dec. 2010.
2008 Workshop on “Faculty Empowerment Program – An Indian Approach”, At Amrita Vishwa Vidyapeetham University, Coimbatore, 25 – 27 January 2008.
2008 Training on Introduction to Abaqus CAE and Standard and Explicit solvers, at Abaqus India (p) Ltd, Bangalore, 25 - 29 August 2008.
2003 Workshop on “Finite Element Analysis and Design of Structures” (FEADS’03), at Structural Engineering Research Center, Chennai, 11 - 12 Dec. 2003.
2003 Advanced Training Program on “MSC.MARC FE Software”, at CSM Software Pvt. Ltd., Bangalore, 8 - 9, Dec. 2003.

Publications

Publication Type: Journal Article

Year of Publication Title

2019

R. Senthil Ku T, BalajeeRamakrishnananda,, Soorya, V., and Dr. Sivakumar V., “Aerodynamic performance estimation of camber morphing airfoil for small unmanned aerial vehicle”, Journal of Aerospace Technology and Management., 2019.

2019

R. Senthil T. Kumar, Narayanaprasad, N., Kumaran, Y., Dr. Sivakumar V., and Ramakrishnananda, B., “Numerical analysis of discrete element camber morphing airfoil in the reynolds number of conventional flyers”, Lecture Notes in Mechanical Engineering, pp. 187-193, 2019.[Abstract]


This paper investigates the aerodynamic performances of an airfoil morphed into another airfoil configuration at a Reynolds number of 3 × 106 using discrete element method. Morphing airfoil configurations were achieved by adjusting three locations along with the chord of NACA 0012. Out of the three, two were chosen at the maximum camber and maximum thickness positions corresponding to that of the target airfoil (NACA 23012). The third position was fixed at 80% of the chord. Six morphed airfoil configurations were generated, and their performances were numerically computed between 0° and 16° angle of attack using ANSYS Fluent v15.0. Spalart–Allmaras and transitional shear stress transport models were used to evaluate the aerodynamic performance of the morphed airfoil configurations. Over this range of angles of attack, morphed configurations were ordered according to three factors—high lift, low drag and high cl/cd. The airfoil can morph from one to another during different phases of flight to give an overall optimum aerodynamic performance. Additionally, the effect of smoothening the sharp corners at the morphing locations is also investigated. © Springer Nature Singapore Pte Ltd. 2019.

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2017

R. Senthil T Kumar, Balaramraja, V., and Dr. Sivakumar V., “Aerodynamics of Discrete Location Camber Morphing Airfoils in Low Reynolds Number Flows”, Indian Journal of Science and Technology, vol. 10, pp. 1-13, 2017.[Abstract]


Objectives: This paper focuses on morphing the base airfoil similar into that of the target airfoil for the application of small unmanned aerial vehicle in low Reynolds number regime. Methods/Statistical Analysis: In this study, discrete location camber morphing approach was used to achieve the morphing configurations of base airfoil. Discrete location camber morphing method was classified into single, two and three location morphing configuration based on the number of morphing locations. The aerodynamic performance of morphed airfoil configurations were studied at the low Reynolds numbers of 2.5 × 10 ⁵ and 3.9 × 10 ⁵ using XFLR5 - e N method. Findings: The base airfoil for this study was selected as NACA0012. The E 207 airfoil which has better aerodynamic performance in low Reynolds number regime was selected as the target airfoil. Eleven different morphing configurations of base airfoil were developed for this study, which falls under these three classifications. Two out of eleven morphed configurations have similar geometric features and equivalent performance as that of E 207 for different range of angles of attack. These two morphed configurations showed a rise of about 3% in maximum aerodynamic efficiency compared to the target airfoil for the tested Reynolds number. Out of these two morphed configurations, one belongs to two location morphing method and another belongs to three location morphing method. This study also reveals that atleast one morphing location has to be closer to maximum camber position of the target airfoil to achieve an effective morphing. There is a possibility for switching between these two morphed configurations as they have two common morphing locations during the flight. Application/Improvements: This type of camber morphing can be positively applied in small unmanned aerial vehicles to achieve better aerodynamic performance over the entire flight mission.

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2017

A. G. Mannadiar, Bhowmik, S., Dr. Sivakumar V., Varshney, L., Kumar, V., and Abraham, M., “Influence of surface activated carbon nano fiber on thermo-mechanical properties of high performance polymeric nano composites”, Journal of Composite Materials, vol. 51, no. 8, pp. 1057-1072, 2017.[Abstract]


This investigation highlights the influence of plasma modified carbon nano fiber (CNF) on the various properties of poly ether ketone (PEK). CNFs were modified with oxygen plasma under low pressure to enhance the interfacial adhesion between the reinforcement and matrix. Significant changes are evident in the elemental composition of oxygen and carbon on the plasma modified CNFs as observed by X-ray photo electron spectroscopy. Based on results from compression and tensile strength, significant change in the mechanical properties of the composites is observed. Dynamic mechanical thermal analysis (DMTA) reveals that the storage modulus increases on reinforcing modified CNF in PEK. The increase in modulus is noticeable only up to 1.5% wt reinforcement of CNF, while higher percentage of reinforcement leads to decline in properties. DMTA studies also clearly shows that the dispersion of CNF is not uniform after 1.5% of CNF reinforcement. However, differential scanning calorimeter and thermo gravimetric analysis studies reveal that the thermal properties of the CNF reinforced composite do not vary significantly. Thermal conductivity results show a substantial increase in the thermal conductivity of polymeric composites on increasing the reinforcements. Transmission electron microscopy (TEM) analysis reveals that there is uniform dispersion of CNF in PEK. TEM also clearly shows that higher percentage of CNF leads to agglomeration. Physico-chemical analysis indicates that the contact angle increases on increasing the reinforcements. These findings would be highly useful to make way for PEK composites for high temperature and high strength application.

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2017

G. Ajeesh, Bhowmik, S., Dr. Sivakumar V., and Varshney, L., “Influence of surface activated carbon nano fibres on mechanical properties of poly ether ketone (PEK)”, IOP Conference Series: Materials Science and Engineering, vol. 204, p. 012010, 2017.[Abstract]


This investigation highlights different surface functionalization processes of Carbon Nano Fibres (CNF’s) and their effects on mechanical properties of Polyetherketone (PEK) nano composite. Surfaces of CNF’s were modified by low pressure plasma process. There is a significant change in physico-chemical characteristics of CNF’s after low plasma treatment as evident from Transmission Electron Microscopy (TEM) and Fourier Transform infrared Spectroscopic (FTIR) studies. Significant modification in surface morphology and oxygen functionalities are observed as a result of surface modification. There is a significant increase in mechanical properties of high performance polymeric nano composites when surface functionalized CNF’s are dispersed in polymeric matrix.

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2017

A. S. Sundaram, Eranezhuth, A. A., Krishna, K. V. V. R., Kumar, P. K., and Dr. Sivakumar V., “Ballistic Impact Performance Study on Thermoset and Thermoplastic Composites”, Journal of Failure Analysis and Prevention, pp. 1-8, 2017.[Abstract]


Ballistic impact-resistant materials are of interest for the past few decades. Ballistic impact is a high-velocity impact where the target material is perforated by the projectile, such as a bullet hitting on a surface. In this study, the effect of ballistic impact on thermoset composites, Kevlar–Epoxy, Carbon–Epoxy, Glass–Epoxy, and thermoplastic composite, Carbon–Polyetheretherketone, was done. Projectile residual velocity and projectile penetration depth were used to quantify the effectiveness of the composite material to resist perforation. The simulation study was done on ABAQUS-6.13. The study included preliminary fiber orientation studies and selection of the best performing composite with the most effective fiber orientation. Further, the selection of the best performing target material was done by varying target thickness and projectile velocity. In this study, high-performance Carbon–Polyetheretherketone composite showed the most impact resistance. © 2017 ASM International

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2017

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.

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2017

Ajeesh G, Dr. Sivakumar V., Shantanu Bhowmik, Lalit Varshney, Kumar, V., and Mathew Abraham, “Effects of High Energy Radiation and Thermo-Chemical Environments on Polyetherimide Composites: Futuristic Approach to Nuclear Waste Storage”, International Journal of Nuclear Energy Science and Technology, 2017.

2016

A. G. Mannadiar, Bhowmik, S., Dr. Sivakumar V., Varshney, L., Baluch, A. H., Park, Y., Gilsang, S., and Kim, C. - G., “Influence of chemically and plasma-functionalized carbon nanotubes on high-performance polymeric nanocomposites”, High Performance Polymers, vol. 28, no. 5, 2016.[Abstract]


This investigation highlights different surface functionalization processes of multi-walled carbon nanotubes (MWCNTs) and their effects on mechanical properties of polyetherimide nanocomposite. Surfaces of MWCNTs were modified by chemical process and by low-pressure plasma process. There is a significant change in physicochemical characteristics of MWCNTs after chemical and low plasma treatment evident from scanning electron microscopy, transmission electron microscopy, and X-ray photoelectron spectroscopy studies. Due to surface modification of CNTs, there is a significant change in surface morphology and increase in oxygen functionalities such as C=O, C–O, and COOH especially evident in low-pressure plasma treatment; however, differential scanning calorimeter and thermogravimetric analysis studies reveal that thermal properties of the composite do not alter as such. There is a significant increase in mechanical properties of high-performance polymeric nanocomposites when surface-functionalized MWCNTs are dispersed in polymeric matrix; however, surface characteristics of the composite remain almost unchanged evident from contact angle and surface energy studies.

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2016

Dr. Sivakumar V., Dani, K. P., and Sriram, S., “Prediction of Stress Intensity Factor on Precracked Composite Wing Rib Made up of Carbon-Epoxy IM7-8552”, Journal of Failure Analysis and Prevention, pp. 1-12, 2016.[Abstract]


The stress intensity factor (SIF), K, is an important parameter to predict the stress state (“stress intensity”) near the tip of a crack caused by a remote load or residual stresses. It can determine the probability of crack propagation and failure of the material. To study the use of high-strength material, IM7/8552 in the crack prone region is the main focus of this present study. A semi-elliptical surface flaw in a typical Boeing-747 rib section having circular cut out and experiencing an in-plane shear loading of 10.21 MPa was considered for analysis. A parametric study on crack initiation is done by having different size of cracks at different locations across the layers. The values of SIF for all the three modes were calculated using the contour integral method. In the present study, we have considered IM7-8552/carbon-epoxy composite due to its high performance and intermediate modulus property. As there are no theoretical solutions for mixed mode loading problems, finite element packages like HYPERMESH and ABAQUS were used to obtain the SIF along the crack edge. The corresponding stress intensity factor values were compared to the fracture toughness of the material to determine the probability of crack initiation. It was observed that the mode of failure changes along with shape of the crack. The analysis results showed a high probability of failure. A comparative study on T300-5208/carbon-epoxy and IM7-8552/carbon-epoxy was performed. IM7-8552/carbon-epoxy composite showed higher resistance to failure. By modifying the fiber orientations, stress concentrations were minimized to a tangible limit.

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2016

Shantanu Bhowmik, .G, A., Dr. Sivakumar V., Lalit Varshney, Kumar, V., and Mathew Abraham, “Feasibility of Polyetherketone (PEK) Composites: A Solution for Long Term Nuclear Waste Storage”, International Journal of Nuclear Energy Science and Technology, vol. 10, no. 3, pp. 257-275, 2016.[Abstract]


This investigation highlights the effect of radiation, chemical and thermal environments on mechanical and thermal properties of polyetherketone (PEK) composites and its rationale for long-term nuclear waste storage. The tests are conducted on samples manufactured using PEK and PEK reinforced with modified carbon nano fibre (CNF). The specimens are subjected to gamma radiation doses of 5 MGy, which is equivalent to the cumulative dosage of radiation from spent nuclear fuel until the radioactivity neutralises completely. Studies under transmission electron microscopy (TEM) reveal that there is a uniform dispersion of modified CNF in PEK. Differential scanning calorimetry (DSC) and thermogravimetric analysis (TGA) indicate that there are no significant changes in thermal properties of PEK and PEK composite when exposed to aggressive environments. It is observed that tensile strength of polymeric samples remains unchanged when exposed to gamma radiation and thermo-chemical environment.

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2016

G. Ajeesh, Shantanu Bhowmik, Dr. Sivakumar V., Lalit, V., Abrar, B., Yurim, P., Son, G., and Chun, G. Kim, “Influence of Chemically and Plasma Functionalized Carbon Nanotubes on High Performance Polymeric Nano Composites (Accepted)”, Journal of High Performance Polymers, vol. 28, no. 5, 2016.[Abstract]


This investigation highlights different surface functionalization processes of multi-walled carbon nanotubes (MWCNTs) and their effects on mechanical properties of polyetherimide nanocomposite. Surfaces of MWCNTs were modified by chemical process and by low-pressure plasma process. There is a significant change in physicochemical characteristics of MWCNTs after chemical and low plasma treatment evident from scanning electron microscopy, transmission electron microscopy, and X-ray photoelectron spectroscopy studies. Due to surface modification of CNTs, there is a significant change in surface morphology and increase in oxygen functionalities such as C=O, C–O, and COOH especially evident in low-pressure plasma treatment; however, differential scanning calorimeter and thermogravimetric analysis studies reveal that thermal properties of the composite do not alter as such. There is a significant increase in mechanical properties of high-performance polymeric nanocomposites when surface-functionalized MWCNTs are dispersed in polymeric matrix; however, surface characteristics of the composite remain almost unchanged evident from contact angle and surface energy studies.

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2015

Dr. Sivakumar V., G. B. Kumar, and Gautham, A., “Crack Initiation Study on Aircraft Composite Rib with Semi-elliptical Surface Flaw”, Journal of Failure Analysis and Prevention, ASM International, Springer, vol. 15, no. 6, 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

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2015

Ajeesh G., Shantanu Bhowmik, Dr. Sivakumar V., Lalit Varshney, and Mathew Abraham, “Investigation on Polyetheretherketone Composite for Long Term Storage of Nuclear Waste”, Journal of Nuclear Materials, 2015.

2015

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.

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2013

Dr. Sivakumar V. and Ramesh, U. N. Asish, “Non-linear 3D Finite Element Analysis of the Femur Bone”, International Journal of Research in Engineering and Technology (IJRET), vol. 2, no. 3, pp. 266-275, 2013.[Abstract]


In this paper a 3D stress analysis on the human femur is carried out with a view of understanding the stress and strain distributions coming into picture during normal day to day activities of a normal human being. This work was based on the third generation standard femur CAD model being provided by Rizzoli Orthopedic Institute. By locating salient geometric features on the CAD model with the VHP (Visible Human Project) femur model, material properties at four crucial locations were calculated and assigned to the current model and carried out a nonlinear analysis using a general purpose finite element software ABAQUS. Simulation of Marten’s study revealed that the highest stress formed in the absence of the cancellous tissue is almost double the value of stress formed with cancellous tissue. A comparative study was made with the Lotz’s model by taking into consideration two different sections near the head and neck of the femur. An exhaustive number of finite element analyses were carried out on the femur model, to simulate the actual scenario.

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2012

Dr. Sivakumar V. and Palaninathan, R., “FE Analysis of Contact Pressure Prediction on O-Rings Used in Solid Rocket Booster Segment Joints”, International Journal of Science and Engineering Applications (IJSEA), vol. 1, no. 1, pp. 8-16, 2012.

2012

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.

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Publication Type: Conference Proceedings

Year of Publication Title

2019

R. Senthil Ku T, V, S., Thayalan K, Parthasarathi A, and Dr. Sivakumar V., “Aerodynamic benefits of flexible morphing airfoil for SUAV”, International Conference on Applied Mechanics and Optimisation, ICAMeO-2019. Mar Baselios Campus, Mar IvaniosVidyanagar, Thiruvananthapuram, Kerala, 2019.

2012

Dr. Sivakumar V., Varughese, B., and Karuppannan, D., “Effect of Skin–Rib Debond on Adhesive Bonded Composite Control Surface of a High Speed Aircraft”, Proceedings of ISAMPE National Conference on Composites, INCCOM11. Amrita Vishwa Vidyapeetham University, Coimbatore, India, 2012.

2011

Dr. Sivakumar V., Balachandran, M., Sreeja, M. R., Ramachandran, K. I., and Bhagawan, S. S., “Optimizing Properties of Natural Rubber for Damping Application Using Design of Experiments”, Proceeding of 5th National Conference on Plastic & Rubber technology (POLYCON-2011). Sri Jayachamarajendra College of Engineering, 2011.

2010

D. Vinesh and Dr. Sivakumar V., “FE Analysis of Interlaminar Stresses in Multilayered Composite Skew Plate With Elliptical Cutout Under Out-of Plane Loading”, Proceedings of 5th International Conference on Theoretical, Applied, Computational and Experimental Mechanics. IIT Kharagpur, pp. 715-718, 2010.

Publication Type: Patent

Year of Publication Title

2017

Shantanu Bhowmik, Govindaraju, M., Ajeesh G, and Dr. Sivakumar V., “Development of Light Weight Blast Proof Composite for Aviation, Space and Defence Structural Applications”, U.S. Patent 2017410463972017.

Publication Type: Conference Paper

Year of Publication Title

2016

Shantanu Bhowmik, Ajeesh G, Dr. Sivakumar V., Lalit Varshney, and Mathew Abraham, “Investigation on High Performance Polymers for Long Term Storage of Nuclear Waste”, in 4th International Conference on Nano and Materials Engineering (ICNME 2016), Bali, Indonesia., 2016.

2008

R. Palaninathan and Dr. Sivakumar V., “Finite Element Analysis of Segment Joint Sealing Efficiency Used in Solid Rocket Boosters”, in International Conference on Aerospace Science and Technology, National Aerospace Laboratory, Bangalore India., 2008.

2007

U. N. Asish Ramesh and Dr. Sivakumar V., “3-D Finite Element Analysis of the Proximal Femur Bone and Nail Implants”, in International Conference on Computer Aided Engineering, IIT Madras. India, 2007.

2005

R. Palaninathan, Arasu, A. Y., Kurian, T., Murugesan, S., and Dr. Sivakumar V., “Bolted and Pin Joints in Solid Rocket Boosters”, in Third M.I.T Conference on Computational Fluid and Solid Mechanics, MIT, Cambridge, USA, 2005.

2005

R. Palaninathan and Dr. Sivakumar V., “Solid Rocket Booster Segment Joints with External Composite Bands”, in International Conference on Computational and Experimental Engineering and Science (ICCES-05), IIT Madras, India, 2005.

2004

R. Palaninathan, Arasu, A. Y., Murugesan, S., and Dr. Sivakumar V., “3-D Stress Analysis of Solid Rocket Booster Segment Joint”, in International Congress on Computational Mechanics & Simulation (ICCMS-04), IIT Kanpur, India, 2004.

1999

Dr. Sivakumar V., Kamesh, J. V., Mangalgiri, P. D., and Upadhya, A. R., “Design of a Capacitance-Type Miniature Accelerometer”, in International Conference on Smart Materials, Structures and Systems, IISC Bangalore. India, 1999.