Nareh

CAREER PROFILE NARESH R  –- – - Employment History: Summary of Experience: 4.8 years of experience in the field of Stress analysis of Airframe Primary Structures. July 16 – August 17 CYIENT. Senior Stress Engineer (Deputed to UTC AEROSPACE SYSTEMS) Non Conformity Repair Concessions - Quality Notification Ground Support Equipment Tool Analysis for Landing Gear Components. To provide Repair Solution for the Manufactured defect by providing its Static and Fatigue Justification. Programs handled: A380, Dash-8, Gulfstream, and A350 Tools used: Abaqus, Goodrich Stress Tools, Catia V5.  Examining the Quality Notification sheets and the attached documents related to the discrepant part provided by customer.  Study the effect of deviation in GD&T parameters and the analysis is carried out with Minimum Material condition.  Involved in Static Strength checks and Fatigue Damage calculation of the Landing Gears parts based on hand calculations and customer provided tools and Abaqus software.  Preparation of Stress Analysis Sheet report in accordance with customer required format on the basis of obtained analysis results to prove the Airworthiness of the part. October 14 – June 16 TATA HAL TECHNOLOGIES. Engineer - Consultant Repair Concessions of Landing Gear Components To provide Repair Solution for the damaged parts of Landing gear - Providing design and stress justification for the acceptance or the non-acceptance of the damaged parts. Programs handled: Single Aisle, Wide Body and Commuter Tools used: PDM, NCODE, MATLAB, In house Fatigue tools  Examining the Repair Concession request sheets including the (Movement Traceability Sheet – History of the part) provided by the customer for the various descriptions of defects in the parts and their drawings.  Technical inspection and conformance of defect descriptions as per the standard drawings and CMM.  Carrying out design analysis for fit, form and function and providing design solution  Identification of sectional properties of the structural component.  Going through stress reports and identification of critical reports, comparing with the repaired part sectional properties and extraction of loads from the critical report.  Calculating various stress parameters to carry out static analysis by Hand calculations and also with the use of client specific tools. Fatigue analysis based on Safe life approach and damage calculation of the part using the Rainflow technique and Miners Rule.  Creating Repair Concession report in accordance with customer required format on the basis of obtained analysis results and to provide schemes to repair the particular damaged part regarding the component usage in aircraft with the perspective of Manufacturing and part service in aircraft. December 12 – September 14 BANGALORE AIRCRAFT INDUSTIRES PVT LTD. Assistant Structural Engineer. Involved in some of the analysis project by using Nastran and Patran software and verifying the results by Hand calculations. The projects involved:  Stress analysis and Fatigue life to crack initiation calculation of a wing bottom skin stiffened panel with a large cutout. A stiffened panel from the transport aircraft wing bottom skin was studied to identify the critical location. Linear static stress analysis of the stiffened panel was carried out. Stress concentration factor and stress distribution near the critical region were obtained through local analysis with more refinement in meshing. 2-D quad and triangular elements were used for meshing the panel. Fatigue life calculation is carried out.  Static and Buckling load carrying capability of the wing box through FEM Approach. Linear buckling analysis of the aircraft wing upper skin panels was carried out. Critical buckling load for each of the panels was calculated using strength of material approach. Linear static analysis of the wing box was carried out to obtain the compressive loads acting at the edge of the panels.  Damage Tolerance Evaluation of a panel with window cutout in the fuselage of a transport aircraft. Damage tolerance evaluation of the stiffened panel consisting of a large cutout for passenger window and bulkheads on either side of the cutout. The maximum tensile stress location was identified. A crack from the highest tensile stress location was initiated in the analytical model of the stiffened panel. Panel was analyzed for different crack lengths by growing the crack in the direction perpendicular to the loading direction. Stress intensity factor calculations were carried out for different crack lengths. Crack arrest capability of the bulkheads on either sides of the window cutout was evaluated analytically by comparing the stress intensity factor values with fracture toughness of the material at different crack lengths. The residual strength diagram was plotted for both fuselage skin and bulkheads to demonstrate the crack arrest capability of the bulkheads through analytical approach. Academic Achievement: Qualification Year of Passing Name of the Institution Percentage B.E (Aeronautical) Intermediate(12th) S.S.C(10th) - Er. Perumal Manimekalai College Sri Chaitanya Junior College Kings English Medium School 8.09 (CGPA) 91.7% 84% Key skills Linear Static Analysis Finite Element Method Hand Calculations Fatigue and Damage tolerance Buckling Projects Landing gear Concessions Fixed wing aircraft Software known MSC Nastran MSC Patran Hypermesh CATIA V5 ABAQUS Personal Data: Date of Birth: Linguistic Ability: Location: 05-Jul-1990 English, Telugu, Tamil & Hindi. Bangalore. (NARESH.R)