Stress / Structural Analysis Engineer

BRUCE T. LI

***** ***** *****, ******** ** ***** 425-***-**** (Cell). E-Mail: ac39hf@r.postjobfree.com

STRESS / STRUCTURAL ANALYSIS ENGINEER

HIGHLIGHT OF QUALIFICATIONS:

•Strong technical skills for strength, fatigue/fracture/durability, damage tolerance, and design allowable/criteria/load development implemented in the structural analysis of composite/metallic aircraft.

•Stress group lead/ focal to provide technical solution/ support and stress report to stress group for the delamination of composite structure, fatigue manual, system structure, and a wide range of structure issues.

•Good structural analysis skill for the following airplane programs:

•Boeing analysis tool: CSW/IAS/SA/SA+/ELFINI/FEADMS/IDTAS/DTANAL(MAGIC)/GKJOINT/THIKAL /JOLT/MSIDComp/FKBEND/APARD/FAMOSS) with Boeing Technical Standards Book (Book 1/2/3/3C/4)/ Boeing Design Manuals (BDM)/ Boeing Structural Repair Manual (SRM)/ Boeing SMA/SDT documents for B737NG, B747-8, B767-200/-300/-400, B777-200ER/-9, and B787-8/-9/-10 airplanes. Great credential in ABAQUS/VCCT (Virtual Crack Closure Technique) -- a Boeing developed technology for predicting fracture and failure in laminated composite materials for the B787 program.

•Airbus analysis tool: ISAMI and design/ analysis manuals for A320NEO, A340-500/-600, and A350-900/-1000 airplanes, and AS350/AS550 Eurocopter. Performed as an integrator to check and to support supplier work for A350-900/-1000 airplanes.

•Sikorsky Aircraft analysis tool: PASA and design/ analysis manuals for CH-53K Helicopter.

•Bombardier Aircraft: design/ analysis manuals for Global 7000 & 8000 airplanes.

•Excellent capability in Finite Element Analysis and computer programming using ABAQUS/PATRAN/NASTRAN/FATIGUE with CATIA V4/V5, Enovia LCA, IVT digital mockup, FEMAP, Pro/Mechanica with Pro/Engineer, I-DEAS, ALGOR, COSMOS/M, ANSYS, Visual Basic, FORTRAN, Unix, and MS Office.

PROFESSIONAL EXPERIENCE:

LJX International Corporation. Mukilteo, Washington

Stress Engineer 5/2016-Present

•Performed the stress analysis of the developing prototype on fuselage and wing structures using FEMAP model with NASTRAN solution and hand calculation for new CX-3A four-seat, single-engine airplane.

Zodiac Aerospace – Advanced Composites Division. Marysville, Washington

Stress Engineer 9/2015-4/2016

•Performed the stress analysis of engine nacelle composite structure (Cascades-UTAS) using FEMAP model with NX NASTRAN solution for Airbus A320NEO airplane.

•Worked on joint structure of composite ultimate and fatigue bearing allowables to apply in engine nacelle composite structure for Airbus A320NEO airplane.

The Boeing Company. Huntsville, Alabama / Everett, Washington

Stress Engineer 4/2015-7/2015

•Developed the stress analysis of the Frame Stabilization and Stringer Clip with joint for 777-9 (777X) fuselage Section 48.

•Performed the damage tolerance analysis on One Piece Frame with fitting for 787-10 fuselage Section 41.

Airbus Americas Engineering, Inc. Wichita, Kansas

Stress Engineer 9/2013-2/2015

•Worked on the development and certification by performing fatigue and damage tolerance analysis using Airbus analysis tool- ISAMI and PATRAN finite element models/ methodologies on Main Landing Gear Support Structure (MLGSS) for A350-900/ -1000 airplanes.

•Managed large finite element models using carbon fiber, copper foil metallic/composite material and provided stress and loads to analysis team by using PATRAN model with NASTRAN solution on cargo and passenger door surrounds structure at fuselage Section 13/14 and Section16/18 for A350-1000 airplane.

•Checked and validated the supplier created DFEM models of cargo and passenger door surrounds structure for A350-1000 airplane.

•Performed the finite element models and report check by using PATRAN model with NASTRAN solution on wing structure for A320NEO airplane.

Safran Engineering Service USA- Aerospace/ Aerostructures Group. Everett, Washington

Sr. Stress Lead Engineer 3/2013-8/2013

•Aerolia- Bombardier Global 7000 & 8000 airplanes: Worked on the integrated product development team (IPDT) for preliminary and detailed sizing analyses at center fuselage hydraulics/ mechanical systems with bracket/ mounting/ platform design and structural analysis.

•Created PATRAN/ NASTRAN and ABAQUS FEM with CATIA V5, and developed detail hand analysis for the fuselage and system structures on Bombardier Global 7000 & 8000 airplanes.

•Eurocopter- Helibras AS350/ 550 rotorcrafts system equipments installation design and structural analysis.

FACC (Fischer Advanced Composite Components) Aerostructures. Seattle, Washington

Stress Engineer 10/2012-3/2013

Work jointly with Aviation Partner Boeing (APB)

•Performed the composite winglet structure analysis with material allowable calculation and bolt joint analysis for B737NG Split Winglet.

•Created PATRAN finite element models with NASTRAN solution for the Split Winglet. Created analysis templates using Excel and Visual Basic tools.

•Performed the composite structure study and analysis for B777-200ER Blended Winglet.

The Boeing Company (KHI). Everett, Washington

Stress Engineer 7/2009-9/2012

B787-9, Section 11 & 45: (3/2010-9/2012)

•Perform the THIKAL/ GKJOINT bolt analysis for over beam lower chord and boomerang fitting on the web of Sloping Pressure Deck for composite Sloping Pressure Deck.

•Calculated the composite hybrid allowables and performed static and fatigue analysis on “Improved Noodle” sections on the composite Sloping Pressure Deck structures.

•Performed the stress analysis of system brackets with metal/ composite material for the composite Horizontal Pressure Deck.

•Performed the fail-safe loads comparison and investigation for composite Horizontal/ Sloping Pressure Deck.

•Performed the stress analysis of stiffener/ clip joint for Section 11 and Section 45 composite Sloping Pressure Deck.

B787-8, Section 45: (9/2009-3/2010)

•Correlated the strain gage predictions on Full Scale Static Test and structure investigation of critical strain gage readings on Horizontal Pressure Deck for composite Horizontal Pressure Deck.

B787-9, Section 45: (7/2009-9/2009)

•Revised the stiffener analysis method on allowables and developed the detail stress analysis activities based on FEADMS/ABAQUS/NASTRAN model for the composite Sloping Pressure Deck.

•Check the joints of stiffener/ tie rod/ gutter with the web of Sloping Pressure Deck using GKJOINT for the composite Sloping Pressure Deck.

Spirit Aerosystems, Inc. Wichita, Kansas (Formerly Boeing’s Wichita Division, before 6/17/2005)

Stress (Focal) Engineer 5/2001-5/2009

CH-53K (Sikorsky Aircraft, US Marine Corps' Helicopter): (1/2009- 5/2009)

•Developed the static and fatigue (NASGRO) analyses on cabin frames, transmission beams and transition joint using Sikorsky’s analysis tool (PASA).

•Performed the detail analysis technique on composite cockpit floor sill and composite skin panel.

B747-8 Advanced Freighter & Passenger, Section 41: (5/2006-1/2009)

•Created the static and fatigue analysis procedures on the skin panel with emphasis on the small hole and large door cutouts using IAS/SA/FEADMS/IDTAS/JOLT tools.

•Worked with Flight Test group in Everett on testing instruments installation to make sure the structure substantiality at the surrounding area. Received the Pride@Boeing award for flight test support.

•Developed the detail analysis methods on the Nose Wheel Well (NWW) and main/ upper deck floor beams.

•Provided design and analysis support on Friction Stir Welding Barrier Beams.

Spirit Fatigue Manual: (11/2006-3/2007) Stress Focal Engineer

•Created Spirit Fatigue Methods and Allowables Manual with emphasis on biaxial/shear/torsion/

bending correction factors, temperature effects, and stress concentration factors.

B787-8, Section 41: (3/2004-9/2005 and 11/2005-5/2006) Stress Focal Engineer

•Evaluated the influence of stringer, shear tie, and frame on residual strength for center crack on composite fuselage skin using PATRAN and ABAQUS/VCCT to determine the tear strap requirement for 24” & 27” frame bay.

•Published Report: Bruce Li (November 2004), "FEA Prediction to Determine the Requirement of Tear Strap for 24”/27” Frame Spacing in Section 41 Fuselage Structure"

•Worked with Structural Damage Technology group in Everett and Seattle on large notch damage for composite skin by using PATRAN and ABAQUS/VCCT for B787 fuselage composite structure.

•Published Report: Bruce Li (May 2004), “FEA Prediction for Large Notch Damage Test of a Graphite/Epoxy Composite Material in Skin Panel & Tear Strap Structure “.

•Developed the detail FEA analysis of large cargo door and small cutouts for composite skin and sub-structure using PATRAN and NASTRAN.

•Performed the damage tolerance analysis on lower sill/latch with composite skin for large cargo door surround structure in composite fuselage using DTANAL/SA/IAS/JOLT tools and BOOK 3 methods (Damage Tolerance Methods and Allowables).

•Created the static and fatigue analysis procedure on the large cargo door surround structure.

•Determined the skin/stringer requirements for fuselage skin buckling.

B767, Section 41: (5/2001-3/2004)

•Fleet support, telex and FAA 8110 form preparation with Interface loads and structural substantiation reports (SCN).

•Customer Intro (Hainan Airlines) for galleys, lavatories, stowage bins, and first class seat (tracks).

•Performed damage tolerance analysis on skin with stringer, NWW, floor beam and frames using DTANAL/SA/IAS/JOLT/ISS Plot /SAMECS with BDM, SRM and BOOK 3 methods.

•Created Standard Work analysis procedure: Damage Tolerance Analysis for B767 Fuselage Skin Repair for Structures Technology group in BCA - Wichita.

•Performed the static and fatigue analyses on the fuselage structure using IAS/SA/ELFINI/JOLT with BDM, SRM and BOOK 1/2/4 methods.

•Approved production design drawings to meet all design and certification.

•Applied and implement requirements of FAR/JAR specifications.

Airbus North America Engineering. Wichita, Kansas

Stress Engineer 9/2005-11/2005

•Worked on the wing structure for A340-500/600 Enhanced program using RAMSAS (Rib Automated Methods for Sizing and Stressing) analysis tools to generate sizing for the generic rib configuration.

CNH Global N. V. (Case Corporation). Wichita, Kansas

Structures Engineer 3/1993-5/2001

•Charged structures analysis for Uni-Loader Skid Steer, Trencher, and Horizontal Drill using Pro/Mechanica/Engineer, NASTRAN/FATIGUE, ALGOR, I-DEAS, ABAQUS and DADS.

ILC Space System Division of ILC Dover, Inc. Houston, Texas

Stress Engineer 1992-1993

•Charged structures analysis for Extravehicular Activity Tool Stowage Device and Tool Crew aids and Tools Stowage Equipment for the Space Station Freedom.

•Generated Finite Element NASTRAN and ALGOR models of various flight hardware and ground structures for stress and transient loads analysis.

Vertex Communication Corporation. Kilgore, Texas

Structures Engineer 1992-1992

•Worked the structural design and analysis of 105 foot antenna for Satellite Communications Earth Station. Utilized SPACE V (Structural Programmed Analysis Capability for Engineer) software program for finite element analysis.

Mactronix, Inc. Dallas, Texas

Product Engineer 1991-1992

•Major responsibilities included: wafer equipments design and improvement.

•Analyzed mechanical, electrical and air valve systems for new product.

EDUCATION:

• The Wichita State University, Wichita, Kansas 12/1990

Master of Science in Aerospace Engineering

Graduate Research Assistant 1986-1990

Thesis: Application of the Boundary Element Method in the Analysis of a Plate with a Repair.

Research: Utilized Finite Element Method with NASTRAN and Boundary Element Method with FORTRAN for Aerospace/Aircraft Structure Applications in Conventional and Composite Materials.

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