Hybrid Rocket Engine Design Optimization at Politecnico di Torino: A Review

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.

On the Multidisciplinary Design of a Hybrid Rocket Launcher with a Composite Overwrapped Pressure Vessel

“…Here, the conventional configuration is considered. The main characteristics of hybrid propulsion systems are the following [7,[11][12][13]:…”

Thickness and uniformity analysis of thin and heat-resistant targets

“…Natural tellurium and germanium were used to save costly isotopes. To define the best parameters for the evaporation (see [10,11] for details), several attempts have been made by varying the evaporation rate, by changing the HOPG substrate thickness and temperature, and using a deposition buffer for helping the diffusion of the evaporated material onto the backing surface. For the materials considered in the present work, the best results were obtained by performing the evaporation process at standard conditions, i.e.…”

“…The uncertainty of these measurements has been estimated around 10%. The APT method was used to characterise the sample in terms of thickness and uniformity, with the set-up hosted at the Department of Applied Science and Technology of the Polytechnic of Turin [11]. The average thickness value was deduced from measuring the energy lost by an alpha particle, emitted by an 241 Am source, in traversing the target.…”

Dynamic Numerical Simulation of Hybrid Rocket Motor with HTPB-Based Fuel with 58% Aluminum Additives

“…The advantages make it suitable for missile systems, attitude control motors, small launch vehicles, and space tourism. The prospect of the hybrid rocket motor is extremely broad [9][10][11][12][13].…”