Job Description Summary: FEA/Aircraft Stress Analysis Engineer
Degree level or equivalent in Aeronautical or Mechanical Engineering preferred, with a minimum of 5 years of experience in Aircraft primary and secondary structures Stress analysis, Composite, and metallic Materials.
Job Description:
Analysis of Metallic & Composite structural components.
Work with a team responsible for the review and analysis of aircraft structural modifications to show compliance to FAR/CAR etc. regulations.
Development of Global Finite Element Model (GFEM) for loads.
Development of DFEM for sizing parts having complex configuration.
Development of Analysis templates using classical methods.
Review technical presentations, interpret the results and present the same to Customer during PDR & CDR gates.
Responsible for ensuring 100% quality and on-time delivery.
Conduct project review meetings to share lessons learned and best practices to improve quality.
Responsible for providing alternative solutions on field issues.
Responsible for process improvements by developing Automation tools.
Work on complex CAE problems to assist product development.
Perform Design Modifications as per need and validating the same with FEA.
Demonstrate Excellent Technical, Interpersonal and Problem-solving skills.
Must have skills:
Expertise in handling various structural analysis tools preferably MSC Nastran/Patran, HyperMesh etc.
2D & 3D Finite Element modeling of simple, moderate and complex components (Plate, Hexahedral & tetrahedral elements) using MSC Nastran/Patran or HyperMesh.
Linear and non-linear static stress analysis (Geometric, Material and contact Linearity) using MSC Nastran/Patran.
Ability to interpret, modify MSC Nastran command statements in bulk data file and re-run analysis; Ability to de-bug FEA errors; perform batch runs for multiple BDFs etc.
Good knowledge of Hand Calculations, able to propose methods for structural failure modes.
Review and understand Strength, stability and Durability requirements of structural components.
Able to perform F&DT analysis.
Should be able to understand/modify TCL macros; Develop MS Excel templates and comprehend VBA in developing automation.
Should be able to propose methodology and strategy for complex metallic and Composites build/update of FE Models in Patran/HyperMesh.
Methods/Process/Procedures similar to Airbus, Boeing, Bombardier and or any defense programmes.
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Degree level or equivalent in Aeronautical or Mechanical Engineering preferred, with a minimum of 5 years of experience in Aircraft primary and secondary structures Stress analysis, Composite, and metallic Materials.
Job Description:
Analysis of Metallic & Composite structural components.
Work with a team responsible for the review and analysis of aircraft structural modifications to show compliance to FAR/CAR etc. regulations.
Development of Global Finite Element Model (GFEM) for loads.
Development of DFEM for sizing parts having complex configuration.
Development of Analysis templates using classical methods.
Review technical presentations, interpret the results and present the same to Customer during PDR & CDR gates.
Responsible for ensuring 100% quality and on-time delivery.
Conduct project review meetings to share lessons learned and best practices to improve quality.
Responsible for providing alternative solutions on field issues.
Responsible for process improvements by developing Automation tools.
Work on complex CAE problems to assist product development.
Perform Design Modifications as per need and validating the same with FEA.
Demonstrate Excellent Technical, Interpersonal and Problem-solving skills.
Must have skills:
Expertise in handling various structural analysis tools preferably MSC Nastran/Patran, HyperMesh etc.
2D & 3D Finite Element modeling of simple, moderate and complex components (Plate, Hexahedral & tetrahedral elements) using MSC Nastran/Patran or HyperMesh.
Linear and non-linear static stress analysis (Geometric, Material and contact Linearity) using MSC Nastran/Patran.
Ability to interpret, modify MSC Nastran command statements in bulk data file and re-run analysis; Ability to de-bug FEA errors; perform batch runs for multiple BDFs etc.
Good knowledge of Hand Calculations, able to propose methods for structural failure modes.
Review and understand Strength, stability and Durability requirements of structural components.
Able to perform F&DT analysis.
Should be able to understand/modify TCL macros; Develop MS Excel templates and comprehend VBA in developing automation.
Should be able to propose methodology and strategy for complex metallic and Composites build/update of FE Models in Patran/HyperMesh.
Methods/Process/Procedures similar to Airbus, Boeing, Bombardier and or any defense programmes.
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