Aeroelasticity and Dynamics of Deployable Space Structures

Deployable space structures rely on flexible materials for folding, stowing, and deployment. In low-gravity or planetary environments, inertial forces, thermal stresses, and environmental interactions (e.g., dust, micrometeoroid impacts) can cause vibrations, buckling, or oscillations that compromise functionality. Unlike rigid components, these structures require careful analysis of coupled structural and dynamic interactions. This project will develop a comprehensive theoretical and computational framework to model these interactions. Key objectives include: Developing mathematical and computational models capturing coupled dynamics of structural deformation, inertial loads, and environmental forces during deployment and operation. Quantifying the influence of structural properties (membrane stiffness, hinge flexibility, mass distribution, damping) on deployment reliability, vibration modes, and functional stability. Exploring strategies to optimize structure design for consistent deployment, long-term stability, and resistance to dynamic perturbations in lunar, Martian, or orbital conditions. Simulating environmental interactions (dust, thermal gradients, micrometeoroid impacts) to predict operational performance and guide material and mechanism selection. Providing insights for mission planning, including deployment sequences, robotic assistance, and structural health monitoring.

Applicants should have or expect a 2.1 honours degree or master’s (or equivalent) in a relevant science or engineering discipline.

Apply online via https://uom.link/pgr-apply-2425
. Specify the project title, supervisor name, funding status, previous study, and two referees. Upload final and interim transcripts, CV, supporting statement, and English language certificate (if applicable). Contact the supervisor for informal enquiries.