Job Description

:

• Stress analysis of metallic and composite aircraft structures using hand calculations, ISAMI, GFEM and DFEMs
• Extraction of loads, stresses, generation of spectra and mission file.
• Extraction of material data, geometry details and fastener specifications from part & assembly drawings.
• Application of appropriate static, fatigue and damage tolerance design values from standard references.
• Creation of FEMs using geometric data from part & assembly drawings.
• Sizing of primary and secondary parts for static and fatigue requirements.
• Fastener load extraction and joint analysis.
• RF calculation for different failure modes such as strength, buckling, shear panel failure, damage tolerance etc.
• Low RF mitigations using classical or numerical methods
• Preparation of stress certification dossiers, ACD4 and ACD6

Requirements:

• B.E / M. E. in Mechanical / Aeronautical Engineering
• 6- 9 years of experience in static analysis (Airbus program A350)
• Graduate / Post Graduate Engineer (Aerospace Engineering / Mechanical Engineering).
• Experience working with Aerospace OEM / Tier / Suppliers on Specific Design activities.
• Minimum 2 years' experience in leading team.
• Tools : Patran/Nastran, Hypermesh, ISAMI (preferred)
• Experience in both metallic and composite material.
• Sound knowledge of structural design principles, aircraft loads and aircraft structures
• Experience in static, fatigue and damage tolerance analysis of aircraft structural components

(Airbus methods and tools would be preferable) * Background in design and sizing of aircraft primary structure components and parts

• Ability to liaise/negotiate with design, stress, EU teams and customer services
• Certification requirements and experience with stress dossiers
• Finite element method / finite element analysis (FEM / FEA)
• Very good analytical and reasoning skills

Sogeclair