Abstract
Optimization of Hybrid Rocket Engines at Politecnico di Torino began in the 1990s. A comprehensive review of the related research activities carried out in the last three decades is here presented. After a brief introduction that retraces driving motivations and the most significant steps of the research path, the more relevant aspects of analysis, modeling and achieved results are illustrated. First, criteria for the propulsion system preliminary design choices (namely the propellant combination, the feed system and the grain design) are summarized and the engine modeling is presented. Then, the authors describe the in-house tools that have been developed and used for coupled trajectory and propulsion system design optimization. Both deterministic and robust-based approaches are presented. The applications that the authors analyzed over the years, starting from simpler hybrid powered sounding rocket to more complex multi-stage launchers, are then presented. Finally, authors’ conclusive remarks on the work done and their future perspective in the context of the optimization of hybrid rocket propulsion systems are reported.
Highlights
The history of trajectory and propulsion system optimization at the Politecnico di Torino (POLITO) begins thanks to the efforts of two brilliant Professors, Giuseppe Bussi and Guido Colasurdo
One of the key features of Hybrid Rocket Engines (HREs) is their relatively low cost when compared to the achievable performance, making a hybrid powered sounding rocket a viable option to transport small payloads to high altitudes, where the absence of the atmosphere allows for micro-gravity conditions that can be experienced in free flight
Concerning the tank pressure histories, the Nitrous OXide (NOX) solution is able to maintain an high pressure level longer than Hydrogen Peroxide (HP) and Liquid OXygen (LOX), due to its self-pressurization capability, resulting in a more regular thrust level. Such behavior holds until the liquid phase exist inside the oxidizer tank (t < 50 s); later the thrust drops and one can observe a change in tank pressure derivative due to the residual gas phase which is fed into the combustion chamber acting as a propellant
Summary
The history of trajectory and propulsion system optimization at the Politecnico di Torino (POLITO) begins thanks to the efforts of two brilliant Professors, Giuseppe Bussi and Guido Colasurdo. His colleague and friend Guido Colasurdo, inspired by this work, started the development of an in-house indirect approach method for trajectory optimization This procedure and its improved versions become the backbone of a great numbers of optimization analysis carried out at POLITO, being able to deal with both impulsive and finite thrust, ascent trajectories, orbit tranfers, rendez-vous, unpowered/powered/aeroassisted flybys, interplanetary missions and debris removal. Due to the strong interdependence of propulsion system performance and specific application, the same approach has been used to carry out coupled optimization of trajectory, propulsion systems design and control [2,3] In this fertile environment, starting from the early 90’s, Hybrid Rocket Engines drew attention of the researchers at POLITO [4].
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