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Esta oportunidade é na àrea de aeronáutica.

In aircraft structural analysis, mass distribution critically impacts the aeroelastic behavior of the model, influencing stability, flutter characteristics, and response to dynamic loads. Effective mass distribution techniques in finite element models (FEM) are essential to achieve reliable simulations, however, high fidelity mass placement is a non trivial issue and presents a challenge in the design phase. This thesis will explore various mass distribution techniques in FEM and their effects on the modal and aeroelastic response of aircraft structures.

Objectives
1. Understand how different mass distribution strategies - e.g., using distributed masses, concentrated masses with offsets, and rigid elements (e.g., RBE2/RBE3) - impact the dynamic and aeroelastic response of FEM aircraft models;

2. Identify methods for optimizing inertia placement and attachment to mitigate spurious local deformation modes and  artificially stiffening the structure for different type of masses of an aircraft: Operational Empty Weight (OWE), payload, fuel, external pods, etc.

3. Design and implement a code/software solution (Matlab, Python, others) that automatically distributes mass properties (total mass, moments of inertia, center of gravity) onto the FEM nodes using specified mass distribution criteria. Test and validate the tool, ensuring it can handle various aircraft sections, structural configurations, and mass input scenarios.

Licenciatura em Engenharia aeronautica ou aeroepsacial.

Altair HyperMesh/HyperView
MATLAB® , Python, VBA 
MSC Nastran / Altair Optistruct

References: Wright, J.R., & Cooper, J.E. (2008). Introduction to Aircraft Aeroelasticity and Loads. John Wiley & Sons.