Simulation-based optimization of DFAN for lift-off environments

The launch of space rockets creates an extremely loud environment due to the sound waves produced by the rocket engine exhaust, which can cause large vibrations in the components of large satellites with a high surface-to-mass ratio. To qualify large satellites for launch, the extreme acoustic conditions are evaluated. To model the sound radiation from the exhaust plume, specialized methods like the Distributed Source Method can be used. However, numerical approaches like the FEM or BEM are not suitable for modelling the sound environments around the fairing due to the large size of the problem and the need for extensive mesh refinements at high frequencies. Instead, geometrical acoustic methods such as ray acoustics are utilized, assuming that sound propagates along rays. This study focuses on predicting the sound pressure levels and directivity patterns around the payload fairing during the lift-off of the VEGA rocket. A predictive algorithm to optimize both the set-up accuracy and power consumption has been treated to provide the physical test and compare the results between the simulated results shown even using the Digital Twin provided by SIEMENS and the ones obtained in the laboratory. In the end, a section of this thesis discusses the design and implementation of the structure that allows the user to provide the acoustic tests.