Structure Stress Engineer - Fatigue and Damage Tolerance
Work Location: Broughton, UK | Duration: Permanent
Skillset - Must have
- Knowledge of Fatigue Design Guidelines, Principles and Methods
- Fatigue Life Calculation
- Crack Propagation Analysis / Damage Tolerance Analysis
- Aware of DT calculation in several different stages like corner crack, through crack, etc.
- Fatigue Criteria for Crack Propagation Analysis to determine the critical crack length
- Awareness and knowledge about the Inspection Techniques for Crack Propagation Analysis
- Detectable Crack Length Determination
- FEA Experience using HYPERMESH, NASTRAN and PATRAN
- Tools NASGRO, MSC NASTRAN, PATRAN, HYPERMESH. ISAMI FDT Tools (1DBJ, 2DBJ, 3DBJ, FASTPPH, CFA)
- Basic Knowledge on CATIA V5
- Microsoft Excel, Word, PPT
Job Description
- Candidate Should have good hand‑on work experience in Fatigue and Damage Tolerance Analysis of Airframe Structural Analysis for aerospace Methods
- Candidate should have in depth knowledge of Fatigue Design Philosophies
- Knowledge and experience in Structural Failure and Fatigue Failure Characteristics
- Aware of various types of fatigue, Fatigue assessment Principles and Methods
- Calculate Fatigue Analysis of Metallic and Fastener parts using AFI method.
- Composite Fatigue Analysis experience
- Candidate should have experience in Damage Tolerance Analysis and Crack Propagation using different NASGRO models
- Identification of PSE (Principal Structural Elements)
- Calculate Stress Concentration Factor (Kt). Wide Spread Fatigue Damage Factor, effect in fatigue due to Size, Material, joints, Machining quality, technology process, etc.
- Fatigue Index Calculation (AFI) Calculation
- Fatigue Equivalent Stress Calculation and extraction of Reference Stresses (1D and 2D Spectrum)
- Fatigue Spectrum Analysis for various mission and Damage Stimulation Analysis
- Fatigue Life Estimation and Damage Tolerance Analysis
- Damage Tolerance Analysis for SLP (Single Load Path), MLP (Multiple Load Path), and DCF (Damage Contaminant Feature) structures
- Initial Crack definition and determination of Critical Crack Length for Airworthiness Limitation Item, Threshold and Inspection Interval
- Low Life Mitigation, various low life mitigation techniques based on OEM based process
- Preparation of Fatigue and Damage Tolerance Analysis Documentation like ACD/ACS/DSD, SCNs and Stress Dossiers
Required Qualifications (Non-negotiable requirements)
- 5–10 years of hands on experience in aerospace structural stress analysis.
- Proven experience working on aircraft programs (A320, A330, A350, A380, etc.).
Personal Competencies
- High analytical skills
- A high degree of initiative and flexibility
- High customer orientation
- High quality awareness
- Excellent verbal and written communication skills
