Assistant Engineer

MURPHY AIDENOGIE

Address: *** *. ****** ******* ****. Apt No 811, Wichita, KS 67212

Phone: +1-708-***-**** Email: ***********@********.*******.*** Webpage: https://www.linkedin.com/in/aidenogiem/

EDUCATIONAL BACKGROUND

Wichita State University, Wichita, Kansas

Graduate Research Assistant, Wichita, Kansas

M.Sc. in Aerospace Engineering (Structures and Solid Mechanics Major) Major GPA: 3.93/4.00 Dec 2018

M.Sc. Thesis: Elastic Wave Propagation through 3-Dimensional Cubic Lattice Structures:

● Performed modal analysis of cubic lattice structures using Comsol Multiphysics, which involved the determination of eigenfrequencies, associated mode shapes and thresholds of their natural resonance.

● Obtained their frequency responses under harmonic loads using ABAQUS EXPLICIT.

● Investigated the optimization of the cubic lattice topology aimed at enhancing the dynamic properties of these structures without a significant mass penalty.

Samara State Aerospace University, Samara, Russia

B.Eng. in Aeronautical Engineering (Aircraft Design & Construction Major) GPA: 4.97/5.00 July 2015

● Capstone project: Design and Structural analysis of wing-fuselage assembly interface of a high-wing heavy lift aircraft.

● Awards: Recipient of the Nigeria-Russia Bilateral Education Agreement Scholarship, Dean's list for excellent academic performance (2011 to 2015 academic years), Olympiad award recipient (in Higher Mathematics, Theoretical Mechanics and Mechanics of Materials)

RELEVANT SKILLS

Software: MSC PATRAN / HYPERMESH / ABAQUS CAE / MSC NASTRAN / OPTISTRUCT / SIMULIA / Comsol Multiphysics / Ansys Mechanical / Solid works / Catia v5 SELECTED PROJECTS/ TRAINING

Wichita State University, Wichita, Kansas

● FAA Laminated Composite Certification Tutorial.

● Damage Tolerance Analysis of a retractable landing gear. Aug 2017

Jan 2016 – May 2016

Samara State Aerospace University (SSAU), Samara, Russia

● Design and stress analysis of a prototype of an amphibious aircraft wing structure (La-8).

● Analytical and FEA Structural Analysis of Aircraft Wings (Yak 42). Jun 2015 – Sept 2015

Feb 2015 – Jun 2015

EXPERIENCE

Aerospace Stress Engineer/ FEM Analyst at Airbus Americas, Wichita, Kansas July 2018-present

● Collaborating with various engineering teams to ensure consensus on Finite Element (FE) analysis approach and conducting checks for FE verification and validation purposes. (A320NEO Flap Track Beams, A330 Rib 11A, A350XWB-900 Under Wing Pylon fittings, A321XLR Outboard Flaps etc.)

● Conducted stiffness sensitivity studies of the proposed modification using MSC NASTRAN / PATRAN / HYPERMESH of the A350XWB-900 &-1000 Main Landing Gear Support Structures (Gear Beam, Side Plates, Fuselage-Link and rear-spar fittings) on the interface loads and updated their GFEM.

● Performed FE analysis and an update of the A321NEO Shroud Box DFEM from the A320 model design using MSC NASTRAN / PATRAN / HYPERMESH.

● Carried out structural optimization studies on the A350XWB EPD fitting using ALTAIR OPTISTRUCT TOOL and HYPERMESH.

● Converted the A350XWB-900 Gear Beam Non-Linear ABAQUS DFEM to a Linear NASTRAN DFEM for basic strength checks, correlated the MSN001 strain gauge test data to the NASTRAN results obtained on the flanges of the Gear Beam and compared the fringe/contour plots of stress, strain, and displacement with the ABAQUS Non- Linear DFEM.

● Performed dynamic analysis of various FE models including modal analysis of the CDR A321XLR Outboard Flap DFEM

● FE model integration of the A321XLR Flap Track Beam 3 & 4 for PDR fatigue & damage tolerance analysis Graduate Teaching Assistant for Vibration Analysis (AE 777) Jan 2017 – May 2018

● Helped with planning, preparation and implementation of activities as directed by the instructor

● Graded assignments and held regular office hours to help students understand the material. Student Designer at the Student Aircraft Design Bureau, Samara, Russia Sept 2014 – Jun 2015

● Designed landing gear structure for a light aircraft from the initial stages of rudimentary conceptual sketch, associated free body diagrams, loading criteria/conditions to hand calculations and using Solid works for final draft.

● Performed iterative FE analysis on structural parts using MSC PATRAN and NASTRAN with the aim of validating their structural integrity while modifying these designed components to reduce weight where necessary.

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