Job Description:

Job scope (core activities):
- Stress analysis of metallic and composite aircraft structures using hand calculations, ISAMI,
GFEM and DFEMs
- Extraction of loads, stresses, generation of spectra and mission files
- 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
Required Domain Expertise:
- 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

Tools: Patran/Nastran, Hypermesh, ISAMI (preferred), AF-Twin, NASGRO, SAFE, DAMTOL
Qualification:
- Graduate/Post graduate (Aerospace / Mechanical / Civil /)
Experience:
- 3-10 years

Soft skills:

- Ability to work independently & in a transnational team.
- Good communication and interpersonal skills
- Flexibility & adaptability