Stress Engineer - Non-linear & Propellants

The Destinus engineering team is seeking a Stress Engineer to support structural sizing and simulation with a focus on non-linear and thermomechanical analysis of solid rocket motor structures.
A core part of this role is the structural simulation of propellant grains, liner bonds, thermal protection systems (TPS), and propellant–liner–casing interfaces – combining FEA with material characterization and test correlation to build substantiated models of energetic material assemblies.
What You’ll Do
· Conduct stress analysis using both classical hand-calculation methods and FEA – linear and non-linear, static and dynamic
· Simulate solid rocket motor structures: propellant grain stress and strain fields, bond integrity at propellant–liner and liner–casing interfaces, TPS thermomechanical response, and igniter/nozzle attachment loads
· Conduct non-linear simulations covering geometric non-linearity, material non-linearity (plasticity, hyperelasticity for propellant and elastomeric materials), and contact mechanics
· Perform thermomechanical analysis across metallic, composite, bonded, and polymeric structures under thermal cycling and operational loads
· Support experimental characterisation of propellant, liner, and bonded joint materials; feed test results (lap shear, peel, tensile, and DMA data) into material models and allowables
· Correlate FE predictions against strain gauge, load, and thermal test data; validate and update models accordingly
· Prepare stress reports, margin-of-safety calculations, and design justification documentation
Requirements
What You’ll Need
· Master’s degree in Aerospace Engineering, Mechanical Engineering, or a related field
· 3–5 years of industry experience in stress analysis of aerospace or mechanical structures
· Proficiency with FEA packages: NASTRAN (Femap or equivalent), Abaqus, or Optistruct/HyperWorks for both linear and non-linear analysis
· Strong classical stress analysis skills: beam theory, buckling, fastener and joint analysis, margin-of-safety calculations
· Experience with non-linear material modelling – plasticity, hyperelasticity, or viscoelasticity; familiarity with propellant or elastomeric material constitutive models is a strong advantage
· Experience with thermomechanical or thermal-structural analysis
· Experience correlating FE predictions with experimental test data
· Background in solid rocket motor, propulsion, or energetic structures is a strong advantage
· Fluent in English; German or French is an advantage

Work arrangement
No