In a worldwide scenario which sees a growing interest of the space market in the use of small satellites (e.g. CubeSats), the scientific community is pushing towards the research of proper miniaturized propulsive systems for attitude, trajectory and orbit control. In particular, novel mission concepts may be unlocked providing the spacecrafts with very precise and rapid manoeuvres capability, that electric thrusters cannot guarantee because of their relatively low thrusts. In this context, chemical propulsion appears to be suitable for this kind of applications. Among the various options, hybrids are garnering significant interest, as they can ensure good specific impulse performance, re-ignition and throttling capability with relative system simplicity, due to the single flow feed line. However, hybrid rocket engines, despite their great potential, remain a highly challenging technology that is currently not used in space missions. In this scenario, the University of Naples “Federico II” (UNINA) is involved in several projects regarding HTP(High-Test Peroxide)-based small-scale hybrid rockets. In the last years, characterization of the internal ballistics of various fuels has been performed, supported by numerical techniques and Computational Fluid Dynamics (CFD) analysis. Polyvinyl Chloride (PVC), High-Density Polyethylene (HDPE) and 3D-printed Acrylonitrile Butadiene Styrene (ABS) have been tested on a 10N hybrid rocket. Experimental results indicate that the regression rate of the fuel is higher than those reported in the literature for similar fuels. This study analyzes the possible causes of this phenomenon from both a fluid-dynamic and thermal perspective. It will be showed that the extensive recirculation zone significantly influences the regression rate. Additionally, the rapid fuel heating leads to a slight increase in the regression rate. The regression laws derived and the proposed insights provide a valuable resource for the design of hybrid thrusters in satellite applications.
Design and Testing of a Hybrid Rocket for Small Spacecraft / Cassese, S.; Mungiguerra, S.; Savino, R.. - (2025). ( AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025 Orlando, Florida, USA 2025) [10.2514/6.2025-1520].
Design and Testing of a Hybrid Rocket for Small Spacecraft
Cassese S.;Mungiguerra S.;Savino R.
2025
Abstract
In a worldwide scenario which sees a growing interest of the space market in the use of small satellites (e.g. CubeSats), the scientific community is pushing towards the research of proper miniaturized propulsive systems for attitude, trajectory and orbit control. In particular, novel mission concepts may be unlocked providing the spacecrafts with very precise and rapid manoeuvres capability, that electric thrusters cannot guarantee because of their relatively low thrusts. In this context, chemical propulsion appears to be suitable for this kind of applications. Among the various options, hybrids are garnering significant interest, as they can ensure good specific impulse performance, re-ignition and throttling capability with relative system simplicity, due to the single flow feed line. However, hybrid rocket engines, despite their great potential, remain a highly challenging technology that is currently not used in space missions. In this scenario, the University of Naples “Federico II” (UNINA) is involved in several projects regarding HTP(High-Test Peroxide)-based small-scale hybrid rockets. In the last years, characterization of the internal ballistics of various fuels has been performed, supported by numerical techniques and Computational Fluid Dynamics (CFD) analysis. Polyvinyl Chloride (PVC), High-Density Polyethylene (HDPE) and 3D-printed Acrylonitrile Butadiene Styrene (ABS) have been tested on a 10N hybrid rocket. Experimental results indicate that the regression rate of the fuel is higher than those reported in the literature for similar fuels. This study analyzes the possible causes of this phenomenon from both a fluid-dynamic and thermal perspective. It will be showed that the extensive recirculation zone significantly influences the regression rate. Additionally, the rapid fuel heating leads to a slight increase in the regression rate. The regression laws derived and the proposed insights provide a valuable resource for the design of hybrid thrusters in satellite applications.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
