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 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 requirement
- 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
- 3 - 5 years of experience in static analysis
- Graduate / Post Graduate Engineer (Aerospace Engineering / Mechanical Engineering).
- Experience working with Aerospace OEM / Tier / Suppliers on Specific Design activities.
- Tools: Patran/Nastran, Hypermesh, ISAMI (preferred)
- 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
Qualification
Bachelor's Degree
Key skill Required
- Aerospace Engineering
- Analysis
- Assembly Drawings
- Design
- Finite Element Analysis
- Geometry
- Hypermesh
- Mechanical Engineering
- Nastran
- Reasoning
- Reasoning Skills
- Static Analysis
- Stress Analysis
- Structural Design
- Tolerance
- Tolerance Analysis
