Job Description:
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Perform stress analysis of metallic and composite aircraft structures using classical methods, ISAMI, GFEM, and DFEM.
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Extract loads, stresses, material data, geometry details, and fastener specifications from part and assembly drawings.
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Apply appropriate static design values from standard references.
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Create and refine Finite Element Models (FEMs) using geometric data.
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Conduct sizing of primary and secondary structures to meet static requirements.
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Extract fastener loads and perform detailed joint analysis. Calculate Reserve Factors (RF) for various failure modes, including:
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Strength
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Buckling (Column & Panel)
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Shear panel failure
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Identify and implement low RF mitigations using classical or numerical methods.
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Prepare stress certification dossiers, including ACD4 and SSR reports.
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Collaborate with design, loads, and certification teams to ensure compliance with regulatory requirements.
Experience: 5-7 Years
This job requires an awareness of any potential compliance risks and a commitment to act with integrity, as the foundation for the Company’s success, reputation and sustainable growth.