Machine learning techniques for flight performance prediction of hybrid rocket engines

This paper investigates the use of neural networks as surrogate models for fast and accurate performance prediction of hybrid rocket engines (HREs). To this aim, a deep feedforward neural network is trained to estimate the thrust and mass flow rate laws of a Liquid Oxygen/Paraffin-wax HRE, as well as other motor characteristics including the burning time, dry and propellant masses, starting from a limited number of motor design parameters, which define the fuel grain and nozzle geometry and the initial oxidizer mass flow rate. A mediumfidelity HRE ballistic model, accounting for nozzle throat erosion and two alternative oxidizer feed systems, a pump-fed system and a pressure-fed system, is used to generate the sample data the network is trained on. A comprehensive analysis is carried out to assess the neural network accuracy and its generalization capability using several network topologies and varying the size of the training set. Finally, to demonstrate the effectiveness of the proposed approach, the trained network is used as surrogate HRE model within a multi-disciplinary optimization process, aimed at determining the optimal HRE design and ascent trajectory for a VEGA-derived three-stage launch vehicle, where the HRE replaces the last two stages of the original four-stage rocket.