Engineer Engineering

Vijay Balasubramaniam.

Mobile: +91-963*******

Email: ***********@*****.***

Master’s in Aerospace Engineering

School of Aeronautics, Technical University of Madrid, Spain October 2013 - July 2014

Bachelor’s in Aeronautical Engineering

Madha Engineering College, Anna University, Chennai, India September 2007 – December 2011

Computing Skills

Engineering tools : Nastran & Patran, Hyper Mesh, ISAMI, Catia V5, Ansys Workbench and MathCAD Programming : Matlab, C, C++

Word Processing : Microsoft Office

OS : Windows & Linux.

6+ Years of experience in the field of airframe components analysis. Engineer:

AXISCADES Engineering Technologies, Airbus Fuselage Design center India (AFDCI). www.axiscades.com

April 2016 – July 2020

Assistant Structural Engineer:

Bangalore Aircraft Industries Ltd.

www.bailindia.com

April 2015 – April 2016

Graduate Engineer trainee:

Bangalore Aircraft Industries Ltd.

www.bailindia.com

January 2012 – May 2013

• Fatigue life estimation using Airbus methodologies (IQF/AFI methods, SAFE and ISAMI tools)

• Finite Element Stress analysis and familiarity with airframe structure

• Buckling analysis using hand calculation and FEA methods

• Basic exposure to GD&T

AXISCADES Engineering Technologies.

Wing Repairs:

Fatigue and damage tolerance justifications for damages on Airbus in-service aircrafts wing structures, damages like Corrosion, Dent, nicks, gouge, rework, etc. Determining the unfactored fatigue life for the damages based on AFI power law (Airbus Fatigue Index) method and other airbus methologies. Tools used: Airbus World, TRM, Knowledge of SRM, SB and Airbus Drawing. Academic Qualifications

Soft Skills

Experience

Technical Skills

Projects

Justification of Airbus Single-Aisle Fuselage Airframe Structures for the Extended Service Goal (ESG) operation:

This project involves providing fatigue justification for the damages on in-service Airbus Single-Aisle fuselage airframe structures during manufacturing (Concessions). The damages are classified into skin reworks, dents, bush installations, rivets changes, stringer and frame repairs etc. Identified damage is justified using Airbus manuals SRM, M2841, AM2235 etc. Perform ‘Dent Analysis’ using ISAMI software and also F&DT software’s like SAFE, to calculate the fatigue lives for the lap and butt joints and spot facing. Determine unfactored fatigue life for the damages based on IQF (Fatigue Quality Index) method. Check whether the damage location is fatigue critical or susceptible for WFD (Wide spread Fatigue Damage) / SB

(Service Bulletin) Determine ISP (Inspection Starting Point) and SMP (Structural Modification Point). Bangalore Aircraft Industries Ltd.

Structural analysis of an Aft fuselage (Empennage) structure, of a transport category aircraft: The work is focused on fatigue calculation, to estimate the fatigue life of the structure under the fluctuating loads experienced during flight. Ensuring the safety of the structure depends by the identification of critical locations for crack initiation. In this project one of the major stress concentration areas in the fuselage is the Rear fuselage portion with a cargo door cut-out region which is considered for the analysis will be analysed. Finite element method (FEM) is used for stress analysis of the aft fuselage structural components.

Hoops stress analysis in Fuselage components and stiffened panel analysis: Linear static stress analysis of fuselage structure for a cabin pressurization load case. Fuselage skin was represented using 2D Quad elements. Stiffening members are represented using 1D element. Global analysis results were considered as bench mark values. Local analysis of the stiffened panel was carried out to identify high tensile stress locations.

Static stress analysis of wing panel with large cut out: Linear static stress analysis of wing box structure was carried out for maximum lift load case. Wing panel with fuel access cut-out was analysed by considering the wing box analysis results as bench mark. Maximum tensile stress location was identified through iterative stress analysis. Stress concentration factor was calculated from the analysis results. Stress distribution around the cut-out was captured through local analysis.

Meshing of airframe components and preparation of input files: Meshing of the airframe components was carried out using MSC Patran/ HYPERMESH. Quality check for the elements to meet the customer’s requirement. Preparation of the finite element input files to be submitted to Nastran for stress analysis. 2 dimensional and 1 dimensional element were used for meshing. I hereby declare that all the details and particulars furnished above are true to the best of my knowledge. Place: Bangalore

Date: 18th

, November, 2020 Vijay Balasubramaniam.

LinkedIn: https://www.linkedin.com/in/vijay-balasubramaniam-ab24059b/ Declaration:

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