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