Hybrid rocket engine design with multi-objective vibrational genetic algorithm

In this study, the conceptual design of a single-stage hybrid rocket engine of a low-altitude sounding rocket is developed using the Multi-Objective Vibrational Genetic Algorithm (MOVGA). A hybrid rocket engine design having single circular port fuel grain with constant cross-section doped with oxidizer is done. Hybrid rocket engine is fueled by Hydroxyl-Terminated Polybutadiene (HTPB) with oxygen as the oxidizer. This is probably the first study in which the MOVGA is used for a hybrid rocket engine design problem. Vibrational genetic algorithm used in the hybrid rocket engine design problem as a comprehensive mutation technique provides diversity in the population in order to explore and find the global optimum quickly. For a high efficient hybrid rocket, the design problem is formulated as maximization of the flight altitude with minimum total mass with engine size (length to diameter ratio) constraint. The algorithm estimates the optimum hybrid rocket engine design including thrust, sizing and flight altitude calculations. Consequently, a mechanical design of a manufacturable and testable hybrid rocket engine is accomplished by means of the MOVGA in reasonable CPU times.