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Smati NEJMEDDINE

Colomiers

Electionseuropéennes 2024

RETROUVEZ GRATUITEMENTLe résultat des européennes à Toulouse ainsi que le résultat des européennes en Haute-Garonne.

En résumé

Senior structural stress analysis engineer with experience in both metallic and composite structures gained in high-tech organizations (Airbus, Fokker, Denel Saab, Latecoere).
Project experience has predominantly involved work on primary aircraft structure, including civilian and military aircraft.

Performed stress analyses and certification documents on empennage, flaps, wing fairing fuselage, nose landing gear bay, fuselage, doors, frames, longitudinal and circumferential junctions, various fittings, and floor structure.

Other attributes:

- Self motivated and conscientious and able to work autonomously as well as in a team

- Rapidly adaptable to new challenges
- Advanced user of MSC.Nastran and Patran including PCL


Mes compétences :
NASTRA PATRAN
UNIX; MathCAD; MS Excel VBA
Catia v5
Aircraft Structures
Hand calculations
FEM analysis

Entreprises

  • STELIA Aerospace - Senior stress engineer

    Colomiers 2015 - maintenant Beluga XL

  • Fokker - Senior Stress engineer

    2014 - 2015 Airbus A350-1000 Flaps.
    Sizing of the track ribs for the A350-1000 outboard flaps from proposal to full-scale development including a weight saving campaign.
    Prepared preliminary stress reports to support work leading up to final certification.

  • Fokker - Stress engineer

    2011 - 2013 Dassault Falcon 5X Empennage.
    Liaised directly with Fokker from preliminary stage design concept to structural justification on both the metallic torque-box ribs and the CFRP skin of the horizontal tail plane (HTP).
    Trade-off studies requiring weight optimisation due to high thermal induced loads in the structure.
    Check of drawings and stress reports.

  • Denel Saab - Stress engineer

    2005 - 2011 Airbus A400M Wing Fairing Fuselage (WFF).
    Worked for Denel Saab on A400M WFF program as a Lead Stress Engineer on the "Onglet'' which is the most intricate part of the WFF.
    A double-curvature composite panel with saddle-type geometry posed some exciting challenges from a stress point of view. The analysis includes substantiation of the sandwich, transition and monolithic regions of the composite panels.
    Optimized metallic sub-structure was designed to strengthen up the whole onglet structure and meet weight requirements.
    Performing hand calculations for all the longitudinal and circumferential junctions of the wing fairing.
    Check of drawings and certification documents for presentation to the client Airbus.

  • Sonaca - Stress engineer

    2004 - 2005 Airbus A380 Nose Upper Shell Fuselage.
    Detailed design concepts for the aluminium frames and skin structure to ensure the integrity of the nose upper shell. Performed longitudinal and circumferential skin splices analysis required to assemble panels. Extracted internal loads using NASTRAN and post-processed stresses and loads using PATRAN and PSN tools (Airbus tools).
    Prepared certification documents and stress reports for presentation to the client Airbus.

  • Airbus - Stress engineer

    Blagnac 2003 - 2004 Airbus A400M Lower Forward Fuselage.
    Liaised directly with Airbus France for preliminary stage design concept to perform a static analysis of the skin reinforcement at the nose landing gear bay cut-out. This analysis aimed to define the size and extension of the cut-out skin reinforcement based on the static strength requirements.

  • Latécoère - Stress engineer

    Toulouse 2001 - 2003 Airbus A380 Lower Forward Fuselage.
    Liaised directly with Airbus France from proposal to full scale development to support the design of the nose landing gear bay and surrounding structure.
    Detailed optimization of the aluminium frames and skin structure to ensure the integrity of the landing gear bay box area.
    In charge of defining the optimum stiffened panel geometry (panels and stringers).
    Both hand calculations and FEM analysis using NASTRAN/PATRAN.
    Drawings release and stress reports up to final certification.

  • Latécoère - Stress engineer

    Toulouse 1999 - 2001 Embraer ERJ-170 Centre Fuselage.
    Developed 3D FEM models for latch fittings on the cargo door using NASTRAN/PATRAN to support static stress and damage tolerance analysis.
    Performed detailed stress analysis on cargo door cut-out and surrounding structures, including door sills and intercostals with drawings release and stress reports.

  • Ratier-Figeac - Stress engineer

    1999 - 1999 Engine CFM56-5 Blade Turbine.
    Developed 3D finite element models of turbine blades and part of the turbofan to evaluate new design concepts for CFM56-5 engine.
    Meshed models with PATRAN, carried out thermo-mechanical and non-linear calculations using SAMCEF code.
    Prepared certification documents and stress reports for presentation to the client.

  • Airbus - Stress engineer

    Blagnac 1998 - 1998 International Space Station Colombus module.
    Designed and analysed detail design concepts for the anti-meteorite shield protection structure of the Columbus Orbital Facilities module for the ISS (composites panels).
    Supported problem-solving efforts in the assembly lines during production.
    Prepared certification documents and stress reports for presentation to the client.

  • Eurocopter - Stress engineer

    1997 - 1997 Airbus Tiger Fighter Helicopter.
    Prepared a numerical model for a bird strike computational simulation analysis with the module MECANO of the SAMCEF code.
    Sized the attachments to transfer the bird impact loads to the surrounding windshield of the Tiger fighter helicopter.

Formations

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