Engineer Project

ANIL DHUPADAL

Email: ***********@*****.*** ~ Contact: +91-937*******

Seeking an assignment as Aeronautical Engineer (Design & Development) with an

Organization of high repute in Aeronautical / Automobile / Energy, Oil & Gas Industry

CAREER CONSPECTUS

1 Over 8 month’s rich & extensive exp. in meshing of aircraft structure.

2Very quick learner, decision-making capability.

3Always try to learn new things and use them whenever needed for the betterment of my work.

4Work in a team with fellow colleagues and can adapt to different working environments.

5Initiative and resourcefulness in responding to job challenges.

CORE COMPETENCIES

Technical Competency

1Sound knowledge of Meshing, using MSC PATRAN, MSC NASTRAN, HYPERMESH

2Good Knowledge of ansys tool.

3Basic Knowledge on strength of materials and FEM.

TECHNICAL SKILLS

1MSC PATRAN

2MSC NASTRAN

3HYPERMESH

4ANSYS

5ABAQUS

CERTIFICATIONS

6Diploma Course (HYPERMESH) on CAD/CAM/CAE (JUNE’11-SEP’11) from EduCADD

Institute, Bangalore-Karnataka, India.

7Diploma Course (ANSYS) on CAD/CAM/CAE (JUNE’11-SEP’11) from EduCADD

Institute, Institute, Bangalore-Karnataka, India.

EXTRA CURRICULAR ACTIVITIES

I was presented paper in a International conference-ICCOMIM on the topic of “Evaluation of

Role of Skin Thickness on Structural Integrity of a Cracked Stiffened Flat Panel” which is

heald in M.S. RAMAIAH INSTITUTE OF TECHNOLOGY on JULY 13, 2012.

M.TECH PROJECT

TITLE: Evaluation of Role of Skin Thickness on Structural Integrity of a

Cracked Stiffened Flat Panel.

In an airframe the thin outer skin is reinforced by stiffeners in two orthogonal directions to

result in a semi-monocoque structure. Stiffened skin panels are, therefore the most generic

structural elements in aircraft. It is very rare that an aircraft meets a structural failure due to an

overload during its service. The most common cause of structural failures is fatigue under

variable amplitude service loading. Fatigue cracks can initiate and propagate to critical

dimensions leading to a catastrophic failure of the airframe.

The current airframe design concepts permit a fatigue crack to initiate from a

manufacturing flaw early in service life and propagate. But it will not lead to a catastrophic

failure of the aircraft. There are number of structural variables that influence the fail-safety of the

airframe based on the above design concept. The skin material plays an important role in this

context.

The aim of this project work is to evaluate the role of skin thickness on the fail-safety of

a cracked airframe. The cracking location is idealized as a flat stiffened panel with a crack

subjected to uniaxial tensile loading. The failure criteria that will be used in this study are

1.The skin crack will have a fast fracture when the maximum stress intensity factor becomes

equal to the fracture toughness of the skin material at that thickness

2.There is no rivet failure

3.There is no failure of the stiffener normal to the crack line

A Finite element analysis approach will be followed in this investigation. Geometrical

dimensions representative of actual aircraft in service will be considered. The skin material will

be taken as 2024-T351 sheet aluminum alloy. A panel strength diagram will be derived from the

stress analysis of this cracked stiffened panel. This diagram illustrates the strength of the skin,

the rivet and the stiffener as function of crack length. A parametric variation of skin thickness

will be carried out.

Key words: Stiffened panel, Stress intensity factor, Fatigue crack, Finite element analysis, fail-

safety, catastrophic failure, Damage Tolerance, Residual strength.

SCHOLASTICS PERSONAL DOSSIER

Average

Qualification Year Institute Board/University

Sikkim Manipal

Disha Academy Univesity (Directorate Pursuing

MBA(Project 2012-14 Banglore Of Distance Education)

Management) Sikkim

76.87%

Dayananda

Vishvesvaraya

M Tech Sagar College (Average of all

Technological

CIM(Mechanical 2010-12 of Engg semesters)

University, Belgaum

Engineering) Banglore

63.08%

Tontadarya Vishvesvaraya

BE Degree (Average of all

College of Technological

(Mechanical 2007-10 semesters)

Engg Gadag University, Belgaum

Engineering)

60.95%

B V VS

Technical (Average of all

Diploma(Mechanical 2004-07 Polytechnic

Education Banglore semester)

Engineering) Bagalkot

PERSONAL DETAILS

Name : ANIL DHUPADAL

Father Name : YAMANAPPA

Date of Birth : 1stAUG 1985

Passport Number : K2653749

Marital Status : Single

Languages Known : English, Hindi & Kannada

Present Address : M.T Jain Student Home, #81, K. R. Road, Shankarpuram, Banglore-

560004

Permanent Address : Anil Dhupadal, post-Asangi, TQ-JamakhandI, Dist-Bagalkot,

KARNATAKA – 587311.

DECLARATION

I solemnly declare the above details furnished are true to the best of my knowledge and belief.

Place : Bangalore Yours Faithfully,

Date : 9-9-2012 (ANIL DHUPADAL)

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