Los Angeles Metropolitan Area
As founder of Laplace Engineering, I have been involved in seeking new potential collaborations to expand our client portfolio and developing strategic partnerships in the aerospace and aviation sectors. I have been involved in internal technical activities such as developing a company comprehensive analysis training for composite analysis, fracture analysis of metallic and composite structure, and finite elements best practices to capture knowledge acquired during more than 18years of work as a structural analyst. As Laplace Engineering Senior Structural Analyst, I am providing analysis support on the following two projects for Kord-Boeing: -SLS Boeing Program Fracture Mechanic team: Preparing Abaqus sub-model of Feedline attachment to LH2 and LOX tanks to evaluate critical rib stresses for fracture mechanic analysis. Sub-models have been run driven by global models. Updating global model loads for fracture mechanic analysis to recover stresses at the different control points of the LH2 and LOX domes. Performing Damage Tolerance Analysis using NASGRO software to verify adequate service life as required from NASA-STD-5019. Creating Beta-Table/Stress intensity factors tables for nonstandard geometry crack using Stresscheck fracture models to implement in NASGRO. -Satellite Division Structural Team: Performing Static and Dynamic analysis using FEM and Hand Calculation of various mechanisms for multiple satellite programs.
787-10/9 Sustaining Team: Rear Spar Integration Team. Evaluation of load increase impact on existing structures, stress analysis of critical components such as Trap Panel using classical hand analysis and FEM (Nastran and Abaqus). Analysis of broadband antenna installation for AAL 787-8. FEM creation and analysis of the different components of the OAE using standard hand calculation and finite element analysis. Impact Analysis of the flight recorder battery cap to the Cargo Liner for MD11 using Abaqus explicit to support the design of a safety protective barrier.
Structural Analyst. Mars 2020 Team – Static, Fatigue and Dynamic Analysis of Mars Rover Components and Sample Catching System using Finite Elements technique and hand analysis. Developed non-linear models in Abaqus to study effect of core break on the drill bit-sample tube by using nonlinear material properties (true stress strain curves). Definition of non-linear stiffness used to apply the loading condition to the bit in order to stabilize the model. Sensitivity study of the friction coefficient effect to the plasticity of the bit and sample tube at the interface with the core. Analysis of Drill Bit Holders - Developed Sub-Assembly Nastran model using linear contacts elements. Size of the different components using detail FEM and hand analysis to support DDR and peer reviews. Analysis of Seal Station components using detail FEM and classical hand analysis methods to support DDR reviews. Creation of Coarse Finite Element Model of the Carousel to be integrated in the Rover Load model to support CLA. Random Analysis of Carousel Doors integrated in the detail subsystem model to evaluate the response.
Performed a Stress evaluation of the Clamshell/sealant installation for the Side of Body Lower Skin/Stringer Joint (Part of the 787 cost saving initiative). The Abaqus submodel has been updated accordingly and the critical pull off failure mode of the stringer run out has been reassessed. Engaged in mentorship for younger engineers by providing guidance on assumptions, evaluations and analytical methods for carbon-reinforced composite and metallic Developed methodology for and performed feasibility study by using the global Abaqus load model of 787-9 Sec.11/Sec.12 Side of body Joints to increase gapping allowable required to maximize rate of production. Static and Fatigue analysis reassessment due to the increase in residual stress. Damage tolerance analysis of the critical locations to ensure no change in the inspection intervals and type of inspections due to the increase in residual stress. Evaluated the residual stress at the wing front and rear spar to SOB joint due to a manufacturing pull-up discrepancy of the fasteners. Using a modified Nastran model, gap elements were introduced with a specific field in the initial opening to simulate the discrepant gapping profile. Residual stress in the TF, RS cap and splice plate have been recovered to reevaluate the static and fatigue M.S. along with the reassessment of the damage tolerance as a first crack model. Developed FEM for door upper seal depressor structure and performed static and fatigue hand analysis using loads generated by the FEM. Performed static fatigue and damage tolerance analysis of 787-9 Sec48 Frame-Shear tie for Certification Report. Working continuously with AR to comply with certification requirements. Performed stress analysis for the 747 – 8I over wing flight test article fairing by using classical hand calculation and Finite Element methods. Performed stress fatigue and damage tolerance analysis to substantiate composite and metallic repairs for 787-8/-9 and 747-8 aircraft models..
Support company effort to produce standard method of analysis. * Create different sections of the Goodrich Stress Office Manual for Composite Stress Analysis such as Composite in Plane Strength, Sandwich panel analysis, Buckling panel analysis, Finite Element Model Guidelines, Composite Bolted Joint Analysis, Cut-out analysis etc. * Support production programs (787 and GTF) with standard Analysis work procedures * Support composite allowable preparation for the different programs based on customer specification Composite Analysis Tool Validation: * Hypersizer™ analysis method validation for composite structure with specific Goodrich analysis methods * Nacelle Component dedicated analysis training using Hypersizer™ * Composite material database template creation