Resume

Sign in

Analysis Engineer

Location:
Kirkland, Washington, United States
Posted:
February 01, 2018

Contact this candidate

Resume:

DEJAN IVOVIC

e-mail: ac4apj@r.postjobfree.com

Phone: 425-***-****

Stress Engineer/Analyst

SUMMARY

- Detail structural analysis employing methods from classic ‘hand’ to detailed FE non-linear analysis

- Detail fatigue analysis spanning from approximate equivalent cycles to full spectrum modeling

- Crack Growth, Residual Strength, Threshold, Fail-Safe Analysis

- Windmilling, Vibration Analysis, Frequency Mode Analysis

- FEA including linear/non-linear, stability, vibration/modal frequency response of composite and metallic structures

- Extensive composite and metallic structure experience

- Strong programming with VBA, Matlab, Python (optimization, templates, connection between different platforms, FEA)

- Stout CAD skills with Catia and working knowledge of UG

EDUCATION

Master of Science in Aeronautics and Astronautics, University of Washington

Bachelor of Sc. in Aeronautical Engineering, University of Belgrade

SKILLS

FEA: Boeing Specific Tools:

Patran / FEMAP, Nastran - 18 years CSW/SWS - 15 years

(101, 103, 105, 106, 111, 400, 600) (Common Structures Workstation)

Abaqus - 4 years IAS - 20 years

Slim / Vision (Lockheed) - 5 years (Integrated Analysis System)

FEADMS (Boeing) - 15 years Various Composite Tools - 10 years

ADAMS - 2 years (Fkbend, Incap, Coramp)

CAD: ADL (Allowable Damage Limits) - 3 years

Catia (4 and 5) - 20 years (Composite Repair)

UG NX - 5 years RDL (Replaceable Damage Limits) - 3 years

Programming Languages: (Composite Repair)

VBA - 15 years BORAT (Composite Repair) - 3 years

MatLab - 8 years IDTAS (Durability) - 15 years

Python - 5 years DTANAL (DT) - 10 years

Report Tools: Lockheed Specific Tools:

Excel - 20 years IDAT - 3 years

MathCad - 15 years IMAT (DT) - 3 years

Data Management Tools: Bombardier Tools of Choice:

Enovia LCA - 12 years NASGRO (DT) - 5 years

PDM / Metaphase - 5 years GOLIHAT (DT) - 2 years

WORK EXPERIENCE:

May 2016 – present Boeing

Department: 787-8/-9/-10 Mid / Aft Body Sustaining

*Providing analysis support for Mid-Aft Body/Final Assembly (e.g. excessive shimming, pull-up, thermal mismatch)

*Working with composite skin/stringers/webs/intercostal, performing delamination/disband/gouge/nicks repairs

*Doing fatigue and DT analysis on Crown and Keel Chords and joints

*FEA modeling/analyzes of circumferential joints that comprise of composite skin/stringer and composite “H” splice fitting

*FEA modeling of circumferential splice to account for misalignment between Section 44 and Section 46 (Patran)

*Performing FEM pull-up study of splice chord against composite bulkhead web due to excessive gaps (Patran)

*New FE FGM to update Superelement with new properties, load cases, and to remodel Ti Fitting into composite (Patran)

April 2012 – March 2016 Boeing

Department: 787-10 Section 11/12 – SOB (Side of Body)

*Completed Analysis (including DT) on RSTF (Rear Spar Terminal Fitting) and Upper/Lower Chord/Splice Joints

*Completed FEA/Fatigue Burst Rotor Blade Windmiling and Frequecny Response Analysis (Patran)

*Sized portions of composite skin, rear spar and splice common to upper and lower RSTF joint interface

Department: 787–9 MTE (Movable Trailing Edge) / MLE (Movable Leading Edge)

*Completed Analysis on Flap Fairings (Hybrid composite, Aramid Nomex core) and created loads Fine Grid FEM (FEMAP)

*Completed Analysis on Leading Edge composite Slats (TEW (Trailing Edge Wedge) Core, Skin Panels)

*Completed Analysis on ADL (Allowable Damage Limit Composites) and FTE RDL (Repairable Damage Limit Composite)

Aug 2011 – April 2012 Bombardier (Shenyang – China)

Department: C-Series 110/130 Rear Barrel

*Completed Analysis on Frames and Frame Splices on Rear Barrel

*Created FEM fine grid detailed fastener model (with non-linear gaps) (FEMAP)

*Created templates (VBA) for Frame Splice Static and Fatigue Checks, GAG Damage Analysis

*Completed DT analysis including WSD (wide spread damage) using NASGRO

Sep 2006 – Aug 2011 Boeing - Fokker

Department: 787-9, Section 45 Pressure Deck

*Sized Inbd/Outbd Runout Beams and their connections to Stub Beams, Longitudinal Beams and Floor Panel

*Sized composite Hat Stiffeners and composite Pressure Deck attached to the Runout Beams

*Completed MOAs (Method of Analysis) and performed Static, Fatigue, DT, and Fail Safe Analysis

*Created detailed local FEA models and performed validation with ILM (Internal Loads Model) (Patran)

Department: 747-8, Flaps

*Completed Analysis on Inboard Flap Details – Main Gimbal Joint and supporting structure

*Performed sizing of Gimbal Fittings, Supporting Ribs, Aft Flap air-load ribs and deflection control ribs

*Performed FEA non-linear large deformation on Flap guide rail (FEMAP)

*Analyzed Joints - composite skin to ribs and composite spars to Gimbal fittings and ribs attachments

*Created detailed FEA fastener models (with non-linear gaps) (FEMAP)

Jun 2005 - Sep 2006 Lockheed Martin

Department: F-35 (JSF)

*Completed Analysis on WCT (Wing Carrie Through) fittings and Arresting Gear details (static, fatigue, DT)

*Worked on FEA model of complete arresting gear mechanism for deformation, loads and vibration (ADAMS)

*Performed FEA study of press-fit joint with the effects of thermal mismatch (FEMAP)

*Created FEM models for deflection sizing (large displacement and plastic curve definition) and stability check (FEMAP)

Sep 2004 - Jun 2005 Boeing

Department: 787-8 Fuselage, Section 44

*Worked on Section 44 composite braided frame structure

Apr 2002 – Aug 2004 Lockheed Martin

Department: Special Mission Aircraft

*Performed structural modification analysis of GV Gulfstream aircraft for the special mission application

*Completed Analysis on floor beams, baggage compartment frame structure, and wing to body composite fairings.

*Developed Excel/VBA templates for various static/fatigue checks

*Created several detail models of composite floor beams and connections to frames (FEMAP)

Aug 1997 – Mar 2002 Boeing

Department: 747 - Fuselage Responsibility Center FRC

777- Wing and Wing to Body Joint

*Worked on 747 Section 46 skin/stringer splices *Supported 777 Wing and Wing to Body production issues

Jul 1993 – Jul 1997 Brampton Engineering, Brampton Canada

Department: High Pressure Blown Film Equipment

*Worked on thermal and pressure analysis on blown film dies and shear flow analysis of matrix plastic



Contact this candidate