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Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.
Francesco Barato. Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages. Aerospace 2021, 8, 190 .
AMA StyleFrancesco Barato. Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages. Aerospace. 2021; 8 (7):190.
Chicago/Turabian StyleFrancesco Barato. 2021. "Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages." Aerospace 8, no. 7: 190.
Hybrid rocket motors have several attracting characteristics such as simplicity, low cost, safety, reliability, environmental friendliness. In particular, hybrid rockets can provide complex and flexible thrust profiles not possible with solid rockets in a simpler way than liquid rockets, controlling only a single fluid. Unfortunately, the drawback of this feature is that the mixture ratio cannot be directly controlled but depends on the specific regression rate law. Therefore, in the general case the mixture ratio changes with time and with throttling. Thrust could also change with time for a fixed oxidizer flow. Moreover, propellant residuals are generated by the mixture ratio shift if the throttling profile is not known in advance. The penalties incurred could be more or less significant depending on the mission profile and requirements. In this paper, some proposed ways to mitigate or eliminate these issues are recalled, quantitatively analysed and compared with the standard case. In particular, the addition of energetic additives to influence the regression rate law, the injection of oxidizer in the post-chamber and the altering-intensity swirling-oxidizer-flow injection are discussed. The first option exploits the pressure dependency of the fuel regression to mitigate the shift during throttling. The other two techniques can control both the mixture ratio and thrust, at least in a certain range, at the expense of an increase of the architecture complexity. Moreover, some other options like pulse width modulation or multi-chamber configuration are also presented. Finally, a review of the techniques to achieve high throttling ratios keeping motor stability and efficiency is also discussed.
Francesco Barato; Elena Toson; Daniele Pavarin. Variations and Control of Thrust and Mixture Ratio in Hybrid Rocket Motors. Advances in Astronautics Science and Technology 2021, 1 -22.
AMA StyleFrancesco Barato, Elena Toson, Daniele Pavarin. Variations and Control of Thrust and Mixture Ratio in Hybrid Rocket Motors. Advances in Astronautics Science and Technology. 2021; ():1-22.
Chicago/Turabian StyleFrancesco Barato; Elena Toson; Daniele Pavarin. 2021. "Variations and Control of Thrust and Mixture Ratio in Hybrid Rocket Motors." Advances in Astronautics Science and Technology , no. : 1-22.
Earth observation is one of the most important satellites’ applications. Past earth observation systems have used traditional space technology to achieve the best possible performance, but have been very expensive. Recently, thanks to advancements in technology and modern microelectronics, small satellites have become more and more useful at much lower costs, even if with reduced performance. The resolution of the optical payload improves as the altitude is reduced. Space system mass is proportional to the cube of the linear dimensions. This means that by flying at lower altitudes, satellites can reduce their payload size and therefore the entire mass of the satellite, thus reducing the cost of the system dramatically. However, almost all the earth observation missions fly at the minimum altitude that provides a sufficient orbital life. The addition of a propulsion system capable of providing drag compensation for the entire satellite operative life provides the possibility to fly at very low earth orbit. In this way, the same performance can be obtained with a smaller and cheaper system. To obtain the same coverage more units are needed to replace a larger unit at higher altitude. In this paper it is confirmed that future smallsat observation systems, operating at a lower altitude than traditional systems, have the potential for comparable or better performance, much lower overall mission cost (by a significant factor), lower risk (both implementation and operations), shorter schedules, lower up-front development cost, more sustainable business model, to be more flexible and resilient, more responsive to both new technologies and changing needs, and to mitigate the problem of orbital debris. This paper focus in particular on the effect of the propulsion system parameters (performance and costs) on the cost model as a function of the altitude. It is demonstrated that new affordable chemical propulsion systems provide already significant benefits with limited constraints, allowing a useful reduction of altitude and, consequently, costs. Electric propulsion systems have the potential to allow even lower altitudes or longer lifetimes; however, they have a stronger impact on the satellite design related to their power consumption, generally requiring deployable solar panels, which can limit the flexibility in the orbit selection or the added weight and cost of batteries. The development of electric thrusters that have good performance and limited impact on the satellite architecture (particularly at small scales) is fundamental to exploit their potential for reduced mission costs through very low altitude flight.
Giacomo Bertolucci; Francesco Barato; Elena Toson; Daniele Pavarin. Impact of propulsion system characteristics on the potential for cost reduction of earth observation missions at very low altitudes. Acta Astronautica 2020, 176, 173 -191.
AMA StyleGiacomo Bertolucci, Francesco Barato, Elena Toson, Daniele Pavarin. Impact of propulsion system characteristics on the potential for cost reduction of earth observation missions at very low altitudes. Acta Astronautica. 2020; 176 ():173-191.
Chicago/Turabian StyleGiacomo Bertolucci; Francesco Barato; Elena Toson; Daniele Pavarin. 2020. "Impact of propulsion system characteristics on the potential for cost reduction of earth observation missions at very low altitudes." Acta Astronautica 176, no. : 173-191.
In the last few decades, vortex injection has been proposed as a possible solution to main hybrid rocket motor drawbacks. The aim of this work is to understand the effects of the swirl intensity and the postchamber length on a 300 N hybrid rocket motor by using H2O2 as the oxidizer and high-density polyethylene as the solid fuel with a classical cylindrical port grain. Three different injection plates have been designed in order to obtain three different geometrical swirl numbers; at the same time, three different postchamber lengths have been used. The numerical and experimental investigations have proved that swirl injection allows a good motor efficiency without the need for a long postchamber. From the analysis of fuel consumption data, a linear relation between the grain surface regression rate and the intensity of the swirling flow given by vortex injection has been obtained. This information could be used in future design phases to tailor the fuel regression in order to achieve the best packaging of a hybrid rocket motor for a desired mission profile.
M. Franco; Francesco Barato; Enrico Paccagnella; M. Santi; A. Battiston; A. Comazzetto; D. Pavarin. Regression Rate Design Tailoring Through Vortex Injection in Hybrid Rocket Motors. Journal of Spacecraft and Rockets 2020, 57, 278 -290.
AMA StyleM. Franco, Francesco Barato, Enrico Paccagnella, M. Santi, A. Battiston, A. Comazzetto, D. Pavarin. Regression Rate Design Tailoring Through Vortex Injection in Hybrid Rocket Motors. Journal of Spacecraft and Rockets. 2020; 57 (2):278-290.
Chicago/Turabian StyleM. Franco; Francesco Barato; Enrico Paccagnella; M. Santi; A. Battiston; A. Comazzetto; D. Pavarin. 2020. "Regression Rate Design Tailoring Through Vortex Injection in Hybrid Rocket Motors." Journal of Spacecraft and Rockets 57, no. 2: 278-290.
Alessandro Ruffin; Enrico Paccagnella; Marco Santi; Francesco Barato; Daniele Pavarin. Real-Time Deep Throttling Tests of a Hydrogen Peroxide Hybrid Rocket Motor. AIAA Propulsion and Energy 2019 Forum 2019, 1 .
AMA StyleAlessandro Ruffin, Enrico Paccagnella, Marco Santi, Francesco Barato, Daniele Pavarin. Real-Time Deep Throttling Tests of a Hydrogen Peroxide Hybrid Rocket Motor. AIAA Propulsion and Energy 2019 Forum. 2019; ():1.
Chicago/Turabian StyleAlessandro Ruffin; Enrico Paccagnella; Marco Santi; Francesco Barato; Daniele Pavarin. 2019. "Real-Time Deep Throttling Tests of a Hydrogen Peroxide Hybrid Rocket Motor." AIAA Propulsion and Energy 2019 Forum , no. : 1.
Marco Santi; Igor Dorgnach; Francesco Barato; Daniele Pavarin. Design and Testing of a 3D Printed 10 N Hydrogen Peroxide Monopropellant Thruster. AIAA Propulsion and Energy 2019 Forum 2019, 1 .
AMA StyleMarco Santi, Igor Dorgnach, Francesco Barato, Daniele Pavarin. Design and Testing of a 3D Printed 10 N Hydrogen Peroxide Monopropellant Thruster. AIAA Propulsion and Energy 2019 Forum. 2019; ():1.
Chicago/Turabian StyleMarco Santi; Igor Dorgnach; Francesco Barato; Daniele Pavarin. 2019. "Design and Testing of a 3D Printed 10 N Hydrogen Peroxide Monopropellant Thruster." AIAA Propulsion and Energy 2019 Forum , no. : 1.
One of the main issues that prevents the widespread use of hybrid propulsion is the low regression rate of classical hybrid fuels. Recently, paraffin-based fuels have been proposed as a viable solution; however, concerns about paraffin thermomechanical properties have often been seen as a possible showstopper. A small-scale hybrid rocket, able to burn hydrogen peroxide and paraffin wax for an extended time, has been designed, built, and tested in order to investigate the suitability of paraffin wax as a hybrid fuel for actual missions. The motor has a nominal burning time of 80 s, which is compatible with the majority of the missions performed by rocket motors. The motor has been tested successfully, demonstrating that paraffin can be used on real missions. Two different types of paraffin were used: type A and type B, which have regression rates of 1.45 and 1.07 mm/s, respectively, at a reference oxidizer mass flux of 50 kg/m2⋅s and at a reference pressure of 15 bar. Moreover, temperature measurements inside the fuel grain demonstrated the liquid layer theory to be valid. An instrumented nozzle has also been used to better investigate the thermal behavior of the nozzle assembly.
Enrico Paccagnella; Marco Santi; Alessandro Ruffin; Francesco Barato; Daniele Pavarin; Gianluigi A. Misté; Giovanni Venturelli; Nicolas Bellomo. Testing of a Long-Burning-Time Paraffin-Based Hybrid Rocket Motor. Journal of Propulsion and Power 2019, 35, 432 -442.
AMA StyleEnrico Paccagnella, Marco Santi, Alessandro Ruffin, Francesco Barato, Daniele Pavarin, Gianluigi A. Misté, Giovanni Venturelli, Nicolas Bellomo. Testing of a Long-Burning-Time Paraffin-Based Hybrid Rocket Motor. Journal of Propulsion and Power. 2019; 35 (2):432-442.
Chicago/Turabian StyleEnrico Paccagnella; Marco Santi; Alessandro Ruffin; Francesco Barato; Daniele Pavarin; Gianluigi A. Misté; Giovanni Venturelli; Nicolas Bellomo. 2019. "Testing of a Long-Burning-Time Paraffin-Based Hybrid Rocket Motor." Journal of Propulsion and Power 35, no. 2: 432-442.
Alessandro Ruffin; Francesco Barato; Enrico Paccagnella; Daniele Pavarin. Development of a Flow Control Valve for a Throttleable Hybrid Rocket Motor and Throttling Fire Tests. 2018 Joint Propulsion Conference 2018, 1 .
AMA StyleAlessandro Ruffin, Francesco Barato, Enrico Paccagnella, Daniele Pavarin. Development of a Flow Control Valve for a Throttleable Hybrid Rocket Motor and Throttling Fire Tests. 2018 Joint Propulsion Conference. 2018; ():1.
Chicago/Turabian StyleAlessandro Ruffin; Francesco Barato; Enrico Paccagnella; Daniele Pavarin. 2018. "Development of a Flow Control Valve for a Throttleable Hybrid Rocket Motor and Throttling Fire Tests." 2018 Joint Propulsion Conference , no. : 1.
Enrico Paccagnella; Francesco Barato; Riccardo Gelain; Daniele Pavarin. CFD Simulations of Self-pressurized Nitrous Oxide Hybrid Rocket Motors. 2018 Joint Propulsion Conference 2018, 1 .
AMA StyleEnrico Paccagnella, Francesco Barato, Riccardo Gelain, Daniele Pavarin. CFD Simulations of Self-pressurized Nitrous Oxide Hybrid Rocket Motors. 2018 Joint Propulsion Conference. 2018; ():1.
Chicago/Turabian StyleEnrico Paccagnella; Francesco Barato; Riccardo Gelain; Daniele Pavarin. 2018. "CFD Simulations of Self-pressurized Nitrous Oxide Hybrid Rocket Motors." 2018 Joint Propulsion Conference , no. : 1.
Hybrid rockets present some disadvantages, mainly low regression rate and combustion inefficiencies. A promising technology to solve both is swirling oxidizer injection, which enhances the wall heat flux and the mixing of the combustion reactants and thus increases the regression rate and the combustion efficiency. A numerical investigation is carried out with a commercial computational fluid dynamics code. This type of analysis can really help with the comprehension of the physical phenomena hidden behind the experimental measurement, and so it can be a powerful aid in the preliminary development and testing of hybrid motors. The first step of this numerical investigation is to study the initial motor geometry, increasing the complexity of the system with the addition of each component one by one to better understand which parameters influence the swirling flowfield inside the combustion chamber. Afterward, a comparison between the axial and swirl injection is done, analyzing the qualitative differences in the flowfields and the quantitative ones in the performance. The central and most important part of this numerical study is focused on the inspection of the motor performance related to several scaling parameters.
Enrico Paccagnella; Francesco Barato; Daniele Pavarin; Arif Karabeyoğlu. Scaling Parameters of Swirling Oxidizer Injection in Hybrid Rocket Motors. Journal of Propulsion and Power 2017, 33, 1 -17.
AMA StyleEnrico Paccagnella, Francesco Barato, Daniele Pavarin, Arif Karabeyoğlu. Scaling Parameters of Swirling Oxidizer Injection in Hybrid Rocket Motors. Journal of Propulsion and Power. 2017; 33 (6):1-17.
Chicago/Turabian StyleEnrico Paccagnella; Francesco Barato; Daniele Pavarin; Arif Karabeyoğlu. 2017. "Scaling Parameters of Swirling Oxidizer Injection in Hybrid Rocket Motors." Journal of Propulsion and Power 33, no. 6: 1-17.
Francesco Barato; Enrico Paccagnella; Daniele Pavarin. Explicit Analytical Equations for Single Port Hybrid Rocket Combustion Chamber Sizing. 53rd AIAA/SAE/ASEE Joint Propulsion Conference 2017, 1 .
AMA StyleFrancesco Barato, Enrico Paccagnella, Daniele Pavarin. Explicit Analytical Equations for Single Port Hybrid Rocket Combustion Chamber Sizing. 53rd AIAA/SAE/ASEE Joint Propulsion Conference. 2017; ():1.
Chicago/Turabian StyleFrancesco Barato; Enrico Paccagnella; Daniele Pavarin. 2017. "Explicit Analytical Equations for Single Port Hybrid Rocket Combustion Chamber Sizing." 53rd AIAA/SAE/ASEE Joint Propulsion Conference , no. : 1.
Marco Santi; Enrico Paccagnella; Alessandro Ruffin; Francesco Barato; Daniele Pavarin; Gianluigi Misté; Giovanni Venturelli; Nicolas Bellomo. Development and Testing of a Long Burning Time Lab-scale Paraffin-based Hybrid Rocket Motor. 53rd AIAA/SAE/ASEE Joint Propulsion Conference 2017, 1 .
AMA StyleMarco Santi, Enrico Paccagnella, Alessandro Ruffin, Francesco Barato, Daniele Pavarin, Gianluigi Misté, Giovanni Venturelli, Nicolas Bellomo. Development and Testing of a Long Burning Time Lab-scale Paraffin-based Hybrid Rocket Motor. 53rd AIAA/SAE/ASEE Joint Propulsion Conference. 2017; ():1.
Chicago/Turabian StyleMarco Santi; Enrico Paccagnella; Alessandro Ruffin; Francesco Barato; Daniele Pavarin; Gianluigi Misté; Giovanni Venturelli; Nicolas Bellomo. 2017. "Development and Testing of a Long Burning Time Lab-scale Paraffin-based Hybrid Rocket Motor." 53rd AIAA/SAE/ASEE Joint Propulsion Conference , no. : 1.
Francesco Barato; Nicolas Bellomo; Daniele Pavarin. Integrated approach for hybrid rocket technology development. Acta Astronautica 2016, 128, 257 -261.
AMA StyleFrancesco Barato, Nicolas Bellomo, Daniele Pavarin. Integrated approach for hybrid rocket technology development. Acta Astronautica. 2016; 128 ():257-261.
Chicago/Turabian StyleFrancesco Barato; Nicolas Bellomo; Daniele Pavarin. 2016. "Integrated approach for hybrid rocket technology development." Acta Astronautica 128, no. : 257-261.
Enrico Paccagnella; Francesco Barato; Daniele Pavarin; Arif M. Karabeyoglu. Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection - Part 2. 52nd AIAA/SAE/ASEE Joint Propulsion Conference 2016, 1 .
AMA StyleEnrico Paccagnella, Francesco Barato, Daniele Pavarin, Arif M. Karabeyoglu. Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection - Part 2. 52nd AIAA/SAE/ASEE Joint Propulsion Conference. 2016; ():1.
Chicago/Turabian StyleEnrico Paccagnella; Francesco Barato; Daniele Pavarin; Arif M. Karabeyoglu. 2016. "Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection - Part 2." 52nd AIAA/SAE/ASEE Joint Propulsion Conference , no. : 1.
CFX software is used to simulate different hybrid rocket configurations, applying liquid N2O as the oxidizer and paraffin as the fuel. This work is the prosecution of a previous paper analyzing liquid injection in a lab-scale hybrid rocket. It is focused on the formulation of the most suitable simulation technique to represent another type of liquid injector, compared with the one described in the previous paper. It also aims at extending the computational fluid dynamics simulation approach to hybrid rockets of larger scales. To validate computational fluid dynamics output, experimental results coming from both a laboratory scale and an increased-scale engine have been used. The different geometries studied include an increased-scale engine with a cylindrical grain having no diaphragm, the same rocket with a one-hole diaphragm inside the fuel grain, and a lab-scale rocket with a one-hole diaphragm. Simulations are steady state, and combustion derives from a single-phase chemical reaction. Liquid injection is fully simulated for the oxidizer, but paraffin entrainment is neglected for the fuel. Computational fluid dynamics results show a good agreement with the corresponding experiments for the ballistic parameters of interest in this study: chamber pressure, efficiency, and C*. Computational fluid dynamics results prove that the simulation technique proposed can be applied to any hybrid rocket scale.
M. Lazzarin; M. Faenza; Francesco Barato; N. Bellomo; A. Bettella; D. Pavarin. Computational Fluid Dynamics Simulation of Hybrid Rockets of Different Scales. Journal of Propulsion and Power 2015, 31, 1458 -1469.
AMA StyleM. Lazzarin, M. Faenza, Francesco Barato, N. Bellomo, A. Bettella, D. Pavarin. Computational Fluid Dynamics Simulation of Hybrid Rockets of Different Scales. Journal of Propulsion and Power. 2015; 31 (5):1458-1469.
Chicago/Turabian StyleM. Lazzarin; M. Faenza; Francesco Barato; N. Bellomo; A. Bettella; D. Pavarin. 2015. "Computational Fluid Dynamics Simulation of Hybrid Rockets of Different Scales." Journal of Propulsion and Power 31, no. 5: 1458-1469.
Enrico Paccagnella; Arif M. Karabeyoglu; Francesco Barato; Daniele Pavarin. Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection. 51st AIAA/SAE/ASEE Joint Propulsion Conference 2015, 1 .
AMA StyleEnrico Paccagnella, Arif M. Karabeyoglu, Francesco Barato, Daniele Pavarin. Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection. 51st AIAA/SAE/ASEE Joint Propulsion Conference. 2015; ():1.
Chicago/Turabian StyleEnrico Paccagnella; Arif M. Karabeyoglu; Francesco Barato; Daniele Pavarin. 2015. "Scaling of Hybrid Rocket Motors with Swirling Oxidizer Injection." 51st AIAA/SAE/ASEE Joint Propulsion Conference , no. : 1.
The study of hybrid rocket transient behavior is a very important issue in order to analyze instabilities and develop throttleable motors. In this paper, an unsteady numerical model is presented. The model is composed of three submodels linked together: 1) zero-dimensional model of the combustion chamber, 2) one-dimensional (1-D) radial model of the fuel grain, and 3) zero-dimensional model of the feeding system. The first model simulates combustion chamber dynamics. The one-dimensional radial model of the fuel grain includes both standard polymeric and liquefying propellants characterized by a melting layer. The fuel block models the heat exchange to the wall, the heat propagation through the solid/liquid phase, and the fuel surface evaporation/entrainment. Finally, the injection system block simulates the unsteady behavior of the feeding line and droplets break-up-evaporation dynamics. In this paper, all the blocks are presented together with their validation versus analytical test cases. For each block, an analysis of the effect of the influencing parameters on the transient thruster behavior is presented.
Francesco Barato; N. Bellomo; M. Faenza; M. Lazzarin; A. Bettella; D. Pavarin. Numerical Model to Analyze Transient Behavior and Instabilities on Hybrid Rocket Motors. Journal of Propulsion and Power 2015, 31, 643 -653.
AMA StyleFrancesco Barato, N. Bellomo, M. Faenza, M. Lazzarin, A. Bettella, D. Pavarin. Numerical Model to Analyze Transient Behavior and Instabilities on Hybrid Rocket Motors. Journal of Propulsion and Power. 2015; 31 (2):643-653.
Chicago/Turabian StyleFrancesco Barato; N. Bellomo; M. Faenza; M. Lazzarin; A. Bettella; D. Pavarin. 2015. "Numerical Model to Analyze Transient Behavior and Instabilities on Hybrid Rocket Motors." Journal of Propulsion and Power 31, no. 2: 643-653.
In this paper, CFX is used to simulate different hybrid rocket configurations applying liquid N2O as the oxidizer and paraffin wax as the fuel. This work is intended as the prosecution of a previous study about hybrid rockets with diaphragms of different geometries inside the combustion chamber, where N2O was injected in a gaseous phase. In this work, liquid injection is introduced, together with droplets vaporization and their coupling with the Eulerian gas phase, in terms of both heat and momentum exchange. The main objective is the description of the numerical models to be applied when liquid is injected. To validate computational fluid dynamics output, experimental results coming from a laboratory scale engine have been used. The different geometries studied include an engine with a cylindrical grain having no diaphragm and the same rocket with a four-hole diaphragm at 24% of the grain length. The simulations are steady state, and combustion derives from a single-phase chemical reaction. Liquid injection is fully simulated for the oxidizer, but paraffin entrainment is neglected for the fuel. Computational fluid dynamics results show a good agreement with the corresponding experiments, concerning the ballistic parameters of interest in this study: chamber pressure, efficiency, and characteristic velocity C*. Computational fluid dynamics predicts (both for gas and liquid injection) a higher efficiency for the rocket geometries provided with a diaphragm compared to the same geometries without a mixing device, and this is in accord with experiments.
M. Lazzarin; M. Faenza; Francesco Barato; N. Bellomo; A. Bettella. Numerical Simulation of Hybrid Rockets Liquid Injection and Comparison with Experiments. Journal of Propulsion and Power 2015, 31, 352 -364.
AMA StyleM. Lazzarin, M. Faenza, Francesco Barato, N. Bellomo, A. Bettella. Numerical Simulation of Hybrid Rockets Liquid Injection and Comparison with Experiments. Journal of Propulsion and Power. 2015; 31 (1):352-364.
Chicago/Turabian StyleM. Lazzarin; M. Faenza; Francesco Barato; N. Bellomo; A. Bettella. 2015. "Numerical Simulation of Hybrid Rockets Liquid Injection and Comparison with Experiments." Journal of Propulsion and Power 31, no. 1: 352-364.
Francesco Barato; Matthias Grosse; Alberto Bettella. Hybrid rocket fuel residuals - an overlooked topic. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014, 1 .
AMA StyleFrancesco Barato, Matthias Grosse, Alberto Bettella. Hybrid rocket fuel residuals - an overlooked topic. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. 2014; ():1.
Chicago/Turabian StyleFrancesco Barato; Matthias Grosse; Alberto Bettella. 2014. "Hybrid rocket fuel residuals - an overlooked topic." 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference , no. : 1.
Nicolas Bellomo; Marta Lazzarin; Francesco Barato; Alberto Bettella; Daniele Pavarin; Matthias Grosse. Investigation of Effect of Diaphragms on the Efficiency of Hybrid Rockets. Journal of Propulsion and Power 2014, 30, 175 -185.
AMA StyleNicolas Bellomo, Marta Lazzarin, Francesco Barato, Alberto Bettella, Daniele Pavarin, Matthias Grosse. Investigation of Effect of Diaphragms on the Efficiency of Hybrid Rockets. Journal of Propulsion and Power. 2014; 30 (1):175-185.
Chicago/Turabian StyleNicolas Bellomo; Marta Lazzarin; Francesco Barato; Alberto Bettella; Daniele Pavarin; Matthias Grosse. 2014. "Investigation of Effect of Diaphragms on the Efficiency of Hybrid Rockets." Journal of Propulsion and Power 30, no. 1: 175-185.