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SOGECLAIR AEROSPACE (91 Courtaboeuf)
- Ingénieur calcul de structures
2015 - 2016
(Toulouse)
A350-1000 Keel Beam composite parts sizing
Sized Keel-Beam PPS composite Ribs in Justification phase and support Lateral Panels and Upper Panel Justification phase calcs. Planning respected, Airbus Quality grade 99%. Use of Excel VBA, Isami V8(Damage Tolerance Transverse Impact, Composite Filled Hole, Unfolding ...), Patran/Nastran (Buckling, Static Analysis)
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SOGECLAIR AEROSPACE (91 Courtaboeuf)
- Responsable Calcul Composite Seat
2014 - 2015
(Toulouse)
Full development and sizing of ZODIAC L3 Composite Seat, Stress lead.
Concepts design and pre-sizing of numerous trade studies to satisfy static, crash, ergonomic, manufacturing, weight and sub-assembly requirements. Hamburg Interior Show specific seat development and sizing with an innovating inclination mechanism. Series solution sizing and metallic parts optimization(Optistruct), Justification stress report. Market 1st composite seat to sustain new crash regulation requirements and correlation of critical sites between real crash and simulation results. Intensive use of Hypermesh and Optistruct solver.
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P3VOITH
- Responsable Calcul PDS
2013 - 2014
(Toulouse)
A350-1000 Pax Door Surround sections 13-14&16-18 co-stress lead.
MatB JDP at Premium Aerospace Augsbourg.
Mat B-C Stress team leading in Toulouse (up to 15engineers), static analysis, Isami and FEM activity.
Composite/ metallic methods evaluations and implementation.
NX Nastran/ Hypermesh software evaluation and stress candidates selection.
Patran/Nastran Sol 101-103-105, condensation, thermal, Isami v8…
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Aviacomp
- Ingénieur calcul de structures
2011 - 2013
(Toulouse)
CSERIES and LEARJET85 Thermoplastic carbon - hybrid and metallic wing fuel tank access covers development and sizing.
Proposed, simulated and tested a new Overmolding shape that was kept on both programs series solution.
Explosive failure test under ultimate pressure witnessing and FEM correlation.
CSERIES and LJ85FTAPS Sizing. Hypermesh, Patran/Nastran Linear Sol 101-Non-linear Sol 106
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Alestis
- Ingénieur calcul de structures
2011 - 2011
(Sevilla)
Transverse stress support on the whole A350-1000 Belly Fairing metallic structure
Design concept review, various parts and assemblies stress analysis (karmans, cross assemblies, rod support fittings…). Patran/Nastran Sol 101, Niu, Bruhn, ESDU, Catia V5
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GKN
- Ingénieur calcul de structures
Arnage
2011 - 2011
(Isle Of Wight)
EMBRAER LEGACY and BOMBARDIER CHALLENGER Nacelles.
Static, thermal, modal and forced vibration analysis for the inlet thermal anti-icing system:
Patran/Nastran Sol 101-103-111.
Fan Cowl Door and Inlet Static, Fatigue and Thermal Stress report check:
Patran/Nastran Sol 101, Niu, Bruhn, ESDU, Peterson, Bombardier Manual, Mathcad
Concessions for static/fatigue calculations on metallic/composite nacelle parts.
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Bombardier Aerospace
- Ingénieur calcul de structures
Montréal
2009 - 2010
(Montreal)
CSERIES Aft-Fuse composite skin/stringers sizing, Stress engineer.
Performed static and buckling analysis to size the carbon monolithic composite Aft Fuse skin/stringers.
Intensive use of Patran/Nastran linear(Sol105) and non linear(Sol106-Sol600).
Performed co-cured skin-stringer super stiffener impact tests to match energy with damage size.
Development of stiffened panel local buckling methodology and various excel VBA tools.
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Bombardier Aerospace
- Ingénieur calcul de structures
Montréal
2006 - 2009
(Montreal)
A330-A340 Systems installation stress certification(OIT, ALNA-V2) and weight variant analysis:
Performed static analysis to certify many modification requests, various systems attach fittings and backup primary structure for A330-200-300/A340-500-600 WP1&2.
A330-200 GMF WP17 sizing:
Sized various lateral pressured floor elements as horizontal links, Y cross beams and seat rail fittings.
Intensive use of Airbus stress software (ASSIST, PSN tools), PATRAN, Bruhn, MTS004,
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Realix
- Ingénieur calcul de structures
2005 - 2006
(Toulouse)
FEM analysis for certification and test correlation for A380-800 cockpit systems.
Performed cockpit 2D-3D systems FEM design, assembly and calculations for modal analysis and static loads interfaces forces determination
Correlated FEM static and modal results with tests results by element properties, interface and modeling hypothesis improvement. Use of Patran/Nastran.
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BEAT
- Ingénieur calcul de structures
2004 - 2005
(Toulouse)
Updated F7X FEM and created local fine FEM.
Modified properties, forms, elements types, transferred loads between models, created historic batchs for iterative modifications, correlated test and FEM results and determined part reaction forces with 3D local models.
Excel VBA/CatiaV4/Elfini.
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BEAT
- Ingénieur calcul de structures
2003 - 2004
(Toulouse)
AIRBUS A380 nose cone 2500VU rack structure sizing (Toulouse).
Performed hand calculations on tension fitting, buckling, bearing, stamping on angle plates, mounts, doors, splices, clevis, lugs, doublers with PATRAN, Bruhn and AIRBUS stress manual.
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BEAT
- Ingénieur calcul de structures
2002 - 2003
(Saint-Cloud)
DASSAULT F7X jet fuselage keel beams pre-sizing.
Sized stiffeners and web by classic calculations and post buckling calculations (shear+compression)
Optimized stiffeners for a mass gain by local FE models.
Excel VBA/ CatiaV4/Elfini/RDM6.
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Anotech
- Ingénieur calcul de structures
2002 - 2002
(Toulouse)
Visual Basic trouble-shooting for A340-500 fuselage central section certification programs
Troubles shooting and development of stress calculation sheets and programs.
Excel VBA.
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Bertin Technologies
- Ingénieur calcul de structures
Montigny-le-Bretonneux
2001 - 2001
(Toulouse+Montigny)
Analyzed and resolved stationary UAV flight instability and in flight behavior issues.
Analyzed flight mechanic and gyroscopic equations, modified the test mock up, prepared and participated to the flying test which isolated the main disturbance cause and obtained the first gas engine mock-up stabilized flights. Use of Excel VBA/Telemetric.
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Sagem
- Projet de fin d'études
PARIS
2001 - 2001
(Cergy-Pontoise)
Optimized the SPERWER UAV composite structure wing:
Reduced 20% of primary structure mass with new composite parts definition
Designed the SPERWER High Velocity mock-up CAO presented to the Bourget Air Show:
Designed of 90% of the SPERWER High Velocity prototype final design
Proposed numerous solutions for new aircraft wing attachments, Graduation Internship:
Proposed nine two parts wings attachment designs for SPERWER LE. Use of Ideas/Excel VBA.
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ABMR
- Stagiaire, Calcul de Structures
2000 - 2000
(Lyon)
Stress analysis for RENAULT VI on plastic parts and robots, EngineerIntenship
Performed linear and non-linear stress calculation of plastic parts, articulated arm robot
Optimized the mass by 15% and wrote french certification stress report. Use of Ideas.
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Sagem
- Stagiaire, technicien données télémetriques
PARIS
1999 - 1999
(Cergy-Pontoise)
SPERWER drone flight data and performances analysis, Technician Internship
Analyzed the telemetry data to quantify the UAV answers to pilot commands. Use of Ezdep/Excel.
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Snecma
- Stagiaire, Ouvier
Courcouronnes
1998 - 1998
(Evry-Corbeille)
Worked on laser welding for CFM56 engines, M53, M88, GE90 as a manual worker.
