Engineer Six Sigma

RUKMIKUMAR PATEL

*****.**@*****.***

Cell: 714-***-****

Objective

Give my best to complete give task, manage it well completing my jobs

responsibilities and contributing the growth of the company.

Education

B.E. Aeronautical Engineering - Gujarat University - India (August 2008)

GPA - 3.76

M.S. Aerospace Engineering - San Diego State University GPA -3.00

Specialization - Structural Mechanics and Composite Materials

Work Experience

Product Development Engineer (MSC Software Corp) QA dept (May

- 2012 - present)

Perform CAE tasks including using the different CAD types, geometry repair

and cleaning, meshing, applying load and boundary conditions, doing the

different types of analysis

. Creating different tests to validate new product development and

certification of new builds

. Develop QA problems for testing features

. Experience in using FEMAP, Nastran and Patran

. Stress analysis in MSC software products to see if the products are

giving correct results or not.

. Perform functional, intergraion, application, regression and

performance tests in a manual and automated environment

. Communicate testing activities with development and other QA teams

across globe

. Writing different test cases, reporting bugs, writing reports and

project management

. Certifying test builds so they can be released.

. Developing and maintaining test cases documentation

. Using and testing all the tools and to see that they do work properly

or not.

. Creating 2d and 3d meshes for different models

Research Assistant (Advanced Materials Processing Laboratory)

(Sep-2010 - April-2012)

Research Topic - Micro Pillar Fabrication

. Study and analyze microstructure, grain boundaries and fracture

analysis using quanta 450 SEM and hardness measurement on different

type's materials and compare them with ASTM standard.

. Used Aluminum, Magnesium and Tin powder and perforated brass sheet as

a substrate to make pillars using our own setup, designed in Solid

Works 2010. Polyethylene glycol (PEG) and water used as a binder. We

sintered green pillars using electric current and furnace under

controlled environment.

. Analysis of joints and sintered joints using FEMAP/NASTRAN.

Manufacturing Engineer (CRS Steels Ltd. Ahmadabad. India)

(June 2008 to June 2009)

. Developed new electro-mechanical system using motor-shaft for faster

and easier operation of the rolling shutters using Solid works and

Pro/E. GD&T of the shutters.

. Designed heavy duty system using high torque power motors.

. Optimized and limited the variables within this system, utilizing

Process Excellence and Six Sigma fundamentals.

. Assisted with the investigation of Corrective/Preventive Actions

(CAPA), notifications and customer complaints, providing solutions

where possible.

. Assisting in seeing if the soldering of the joints and soldering of

the different metallic structure has been done properly.

Graduate Projects

FINITE ELEMENT ANALYSIS OF HEXAGONAL AIRCRAFT WING BOX

. Successfully modeled the aircraft hexagonal wing box using FEMAP with

FAR standards.

. Done the static and buckling analysis of the wing box using NASTRAN

finite element code.

. Meshing of the whole wing box using the QUAD4 elements and the Bar

elements.

Finite Element Analysis & Design of a Plate with Hole

. Modeled one quarter of the symmetric plate with centrally located hole

subjected to uniaxial

tension - using FEMAP.

. Cases of Unstructured, Structured and Non-Uniform meshes were analyzed

using NX NASTRAN.

. Analysis results were compared to the results from hand calculated

elasticity solution.

Modal Analysis of the Aircraft Wing box

. Using the FEMAP and NASTRAN successfully modeled the wing box.

. Done the modal analysis of the wing box to find out the different

modes of the wing box under different type of loading conditions and

different types of loads.

. Found out how we can compare our modes for the different conditions

easily and thus find out our results from which we find out the how

the ribs increase the torsional stiffness and thus helps the wing-box

structure from failing.

Structural Sizing Optimization of aircraft wing box

. Using FEMAP and NASTRAN created 25 different analyses of different

thickness, height and width for the data collection to do the

optimization to check which will be the most efficient and less

weighted structure. Done mesh morphing.

. Project was about structural sizing of wing box, the model analysis of

wing box structure is done using commercial finite element code. We do

25 analyses based on different thickness of design variable based on

latin hypercube sampling and then use curve fitting process to find

best design which satisfies all constrains or smallest margin

violation and under feasible region.

. Successfully reduced the weight of the wing box from 60 kg to 44.112kg

using this optimization technique.

. Optimized the wing box of aircraft for weight reduction using response

surface model.

. Studied topology optimization during the structural optimization

class.

MATLAB code for the analysis of the composite material

. Made a matlab code that can do the whole structural analysis of the

composite material in detail.

. Code gives the extensional stiffness matrix [A], the extension-bending

coupling matrix [B] and the bend-twist coupling matrix [D].

. For a given load set of Nxx, Nyy, Nxy Mxx, Myy, Mxy the code will

find the normal strains and the flexural strains i.e. the bending

curvatures and will also find the Stress and Strains at the bottom and

the top surface of each given ply using the classical plate theory

model.

Analysis of a plate loaded in a localized area of the bottom surface

. Made the plate in the FEMAP and using NASTRAN with load applied on the

bottom surface in a particular localized area.

. Compared data with analytical solutions & commercial finite element

code and try compare the answers obtained by each of the case. Thus

checking the validity of both of the cases. We find the displacement,

stress and the thickness integrated forces and bending moments.

. Successfully checked that the non dimensional displacement of the

plate was same using NASTRAN and matlab.

Relevant coursework

Finite Element Methods in Aero Structures, Vibration of Elastic Solids,

Theory of Elasticity, Mechanical Behavior of Engg Materials, Methods of

Analysis, Structural Optimization, Analysis of Elastic Plates, Composite

Structural Analysis, Incompressible Aerodynamics, CFD 1 &2, Propulsion 1&2,

Aero Structure 1&2, Manufacturing Processes, Solid Modeling.

COMPUTER SKILLS

Operating System: Win 2000/Xp/Vista/7, Mac OS X

Programming Languages: C, MATLAB, FORTRAN, MAPLE, MS-EXCEL

CAE Tools: Solid Works, Patran, MSC SimX FEMAP/NASTRAN, Hypermesh, Catia

V5

Other: Microsoft Office Suite Products

Reference available upon request.

Contact this candidate