Dayanand

CURRICULUM VITAE DAYANAND PATIL C/O, M. Nanjayya, U/30, 2nd Floor, Near Nippan Electronics, K. G. Nagar, BANGALORE – 560019 ________________________________________________________________________ Objective: Currently I am working as a Consultant (P3) on CAE domain. I have an overall experience of 7+ Yrs. in CAE domain. I have been working on aerospace engines platform since December-07 to till date, as Application Engineer in C.S.M Software Company, supported MSC products (MSC Patran/Nastran, MSC Fatigue) from January 2005 till December 2007. To work in a challenging environment that provides opportunity to learn key technologies, be an effective team builder in developing, managing projects and to be an asset for the organization by delivering to the best of my capabilities. Competences Domain: Aeronautical: Worked in static, modal, dynamic, buckling, Non-linear, and Composite Laminate modular modules using MSC. Nastran solver. Over all Responsibilities Handled • Leading team of CAE Stress group • Customer Support. • Pre & Post Sales supports. • Involved in hand calculation. • Executing Engineering Consultancy Project • Corporate Training on basic and advanced MSC. Nastran/Patran and MSC. Fatigue software’s. Awards Received: • Project star for the Q2 of the year 2009 Technical Skills Tools: MSC.Nastran, MSC. Patran 2007r2, Hyper mesh, Cativa v5/r13 Languages: C, PCL (Patran Command language) Environment: Solaris, IRIX, AIX, Linux, Windows NT/9X/2K/XP Education • Master of Technology in Machine Design (Waiting for results), from visvesvaraya technological university (2006 up till this date). • Bachelor of Engineering in Mechanical (65.4%, aggregate), from visvesvaraya technological university (1998 to 2003). • Diploma in Mechanical Engineering (1995 to 1997). Work Experience: From October 2009 till this date Sogeti/Capgemini (DEC 2007 to this Date) SNECMA PCL development for the Convergence checking through customized tool creation. • Extract Von Mises stress (Option Average). • Extract Von Mises stress( Option Difference ) • Calculate the Ratio of Average/Difference. • Crate a field of the node vs ratio. • Crate a temperature load. • Plot the temperature with a 4 values spectrum. Tools Used: MSC. Patran. From December 2008 to August 2009 Sogeti/Capgemini (DEC 2007 to this Date) SNECMA Optimization of Open Blade Rotor (Ver 2.1 to Ver 2.10bis): • Study the preliminary design of an open rotor blade. • Apply the knowledge, application and integration of aerodynamics, temperature, rotation speed and study the structural integrity of different open blade design. • Compare the results, do Hand calculation of the different open blade and choose the optimum blade. • Lead the Team Tools Used: MSC. Patran, Samcef, Campbell, MS Word, MS Excel. From January 2008 to November 2008 Sogeti/Capgemini (DEC 2007 to this Date) SNECMA Life Evaluation on LPT Turbine disk and flange (D1,FL1D1,D2,FL3D3,D3,FL4D4,D4) • Probabilistic analysis in a consistent and convenient manner to facilitate remaining life evaluation of LPT turbine. • The constraint, aerodynamic pressure, cavity pressure, temperature and inertia load are applied to the model. • Convergence study, correlation, crack initiation and crack propagation study. • Lead the Team. Tools Used: MSC. Patran, Samcef, Toscan, MS Word, MS Excel. From August 2007 to October 2007 C.S.M Software (Jan 2005 to Dec 2007) HAL-ARDC Static and Non-Linear Static Analysis of a Composite • Determine the stress, displacement, strength ratio, failure ratio for the CRPF sandwich panel. • Hybrid mesh of CQUAD4 for steel panels and CHEXA 8 as core was meshed. • Enforced displacements, Pressure, temperature were the load applied to the model along with non-linear static analysis. Tolls: MSC. Patran, MSC. Nastran. From May 2007 to July 2007 C.S.M Software (Jan 2005 to Dec 2007) BEL BANGALORE Random Response Analysis Mounting Tray: • Located in the fuselage of the aircraft consisting of shock mount, vertical and horizontal stiffeners. • This assembly was subjected to sever environmental loads such as static and random loads. • The load inputs were supplied as acceleration time histories and the PSD. Tolls: MSC. Patran, MSC. Nastran. From December 2006 to February 2007 C.S.M Software (Jan 2005 to Dec 2007) AIRBUS (EADS) Non Linear analysis of Oil tank door and LAP structures done for EADS (AIRBUS): • Oil Tank door and LAP structures are structural components off the fan cowl. • Finite element model generation using CQUAD, CGAP and CELAS and CHEXA elements. Define composite properties for the structures which are attached to the global FEM model. Strength checking of the structures, profiles and rivets associated with the structure was carried out, using various EADS software’s and few analytically. The above structures were also checked for strength capability to support ultimate or limit loads with the damages occurred after the lightning strike. • Documentation of the structure done for certification purpose. Tolls: MSC. Patran, MSC. Nastran, Hypermesh. From December 2005 to March 2006 C.S.M Software (Jan 2005 to Dec 2007) ARAI Comparative study of results for automotive component with complete and condensed model using with and without superelement technique: • The benchmark was primarily meant to do the comparative study of results of full model and with that of the subcomponent condensed to the main component by superelement technique. • The comparative study was conducted for SOL -111, the main model was constrained and the subcomponent on which load was acting had to be redesign until the desired stress is attained. • So in order to avoid rerunning the whole model each time we condensed the main model and that condensed model was attached to the subcomponent. Tolls: MSC. Patran, MSC. Nastran. From October 2005 to November 2005 C.S.M Software (Jan 2005 to Dec 2007) AIRBUS Finite Element Modeling of Airbus A400M Wing box Ribs. • The project involved the FE model preparation of wing box ribs of Airbus A400M aircraft. The given CATIA model data is converted to IGES format in CATIA and FEM model is prepared to the required specification. • Stiffener part is meshed to the mid plane and web portion is meshed to the bottom plane and different thickness is given to the specified regions as per the given CATIA model. • A static analysis for five load cases was carried out. Tolls: MSC. Patran, MSC. Nastran. From February 2005 to August 2005 C.S.M Software (Jan 2005 to Dec 2007) AIRBUS (EADS) Static Analysis of Pylon Structures done for EADS (AIRBUS) : • Pylon structures are connected to the pod and are used for refueling the aircraft. • To validate structures for the allowable within the limits by comparing with aluminum material and the composite materials, and also obtain the reserve factor for all the components greater than or equal to one. • Documentation for the structure with all iterations performed and final result validation document done for certification. Tolls: MSC. Patran, MSC. Nastran. From December 2003 to May 2004 HAL-ARDC, Bangalore (July 2003 to Dec 2004) HAL-ARDC Stress and Fatigue Analysis of Critical Splice Between Front & Rear Fuselage of Trainer Aircraft • Front fuselage is connected to rear fuselage-using splices at different locations. • The joints at the top sections experience predominantly tensile loads & at the bottom section experience compressive loads. The majority of the load on the splice is shared by the Top Longeron and Spine. • Load on the Splice is obtained from global FE analysis of the fuselage. • Maximum resultant load on the component is divided by the number of rivets in the splice region. • Fatigue analysis is carried using MSC/FATIGUE using S-N approach Tools Used: MSC. Patran, MSC. Nastran, MSC. Fatigue. From July 2004 to November 2004 HAL-ARDC, Bangalore (July 2003 to Dec 2004) HAL-ARDC Stress and Fatigue Analysis of Engine Mount and its Attachment of a Trainer Aircraft: • Engine mount is situated in the rear portion of the aircraft. It is used to support the engine. • The reactions are obtained for engine off and on conditions. • Load spectrums used was symmetric and spin. • Results of all the components meet the fatigue life requirement of the trainer aircraft. Tools Used: MSC. Patran, MSC. Nastran, MSC. Fatigue. Training /Certification: • Training on MSC. Nastran/Patran. • Attended the Advanced Dynamic training by MSC. • Attended the Flight load and Dynamic training for MSC. • Attended the Fatigue training by MSC. Other Activities: Invited Lectures / Talks • Imparted frequent training programs on Basics of Finite Element Method, Linear • Vibrations, Basics of Fatigue, Frequency Response analysis, Nonlinear Analysis, • Transient Analysis to various corporate organizations like: • Indian Satellite Research Organization ( ISRO ), Bangalore. • Hindustan Aeronautics Limited ( HAL ) ARDC, Bangalore. • Hindustan Aeronautics Limited ( HAL ) RWRDC, Bangalore. • Bharat Heavy Electricals Limited (BHEL) Research and Development Centre, • Hyderabad. • Bharat Electronics Limited (BEL), Bangalore. • Tata Consultancy Centre ( TCS ), Bangalore. • Satyam Development Centre, Bangalore. • Infosys, Bangalore. • Arvin Meritor, Bangalore. • Altair Engineering Service, Bangalore. • Indian Institute of Technology, IITMADRAS, Chennai. • Madras Institute of Technology ( MIT ), Chennai. Parallel Processing • DMP (Distributed Memory Parallel) setup and performance tuning in cluster mode and in single machine with multiple CPU. • Configuring SMP (Shared Memory Parallel) in Linux UNIX OS in SGI, AIX, SOLARIS, HP and Windows machines and performance tuning. MSC Adams MSC Nastran Integration • Preformed the modal analysis for the rigid/flexible body and generated the MNF file for the MSC Adams and compared the result Eigen value results that in MSC Nastran and MSC Adams. Nonlinear Buckling • Performed the linear buckling and Non-Linear buckling through the restart and found the critical buckling factor. PCL Macro • Created the customized tool specific to the project and got appreciation from front office. Contact Details: Permanent Address 5th main, Near Joshi farm, Plot no 87, Dharwad = 08. Email Birth Date 12TH – November 1977 Residence BANGALORE Marital Status Married Gender Male Passport Details E7922455