Special Issue “Advances in Hybrid Rocket Technology and Related Analysis Methodologies”

Carmicino, Carmine

doi:10.3390/aerospace6120128

Cited by 14 publications

(3 citation statements)

References 18 publications

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“…More on the evolution of the technology in its early decades, when less knowledge on burn rate modeling and its enhancement was present, can be found in [5][6][7][8]. Recent advances led to increased interest in hybrid rocket systems [9][10][11]. In the 21st century, hybrid propulsion became an attractive solution for various technology applications, often not envisaged earlier.…”

Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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“…This special issue on hybrid rockets, which follows on the heels of "Advances in Hybrid Rocket Technology and Related Analytical Methods" [21], brings together 11 papers from authors around the world. Overall, this second edition is of great value as it continues to provide the technical community with useful information on the subject and extends the current level of knowledge with new technical content, as in the previous issue.…”

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confidence: 99%

Special Issue “Hybrid Rocket (Volume II)”

2022

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“…rocket technology constitutes both a low-cost and a high-performance solution (theoretical vacuum specific impulse being superior to 300 s for certain couples) for a space propulsion system when compared with its rocket propulsion counterparts (liquid and solid), allowing to reduce the manufacturing and production costs while maintaining a great deal in safety and throttability. These advantages lead to the application of hybrid space propulsion systems for sounding rockets, small satellite launchers or even orbital propulsion systems [1]. This technology is characterized by the combustion of two propellants stored at different states of matter: generally, the oxidizer, stored at the liquid or gaseous state is introduced into the combustion chamber by an injection system, where the carburant is stored at the solid state.…”

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confidence: 99%

Pseudo-Two-Dimensional Modeling and Validation of a Hybrid Rocket Combustion Chamber

Granado

Hijlkema

Lestrade

et al. 2022

Journal of Propulsion and Power

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A pseudo 2-D model for the cylindrical combustion chamber of a hybrid rocket is developed in this article with the purpose of its integration in a system design tool used for engine predesign phases. A compromise of simplicity and accuracy is thus required. Integral transient boundary layer equations are included and coupled with the mass and energy balances at the fuel surface, where fuel pyrolysis is described by an Arrhenius law. Studies assessing the model in the non-reactive case provide satisfactory results regarding the description of the boundary layer. Concerning the hybrid case, the computed steady-state fuel regression rates are found to be in the low region of the reference values coming from semiempirical laws for several oxidizer/fuel couples and oxidizer mass fluxes, producing errors up to 50% for certain sources. The effect of mass flux and motor size is correctly simulated. Eventually, the whole engine operation is assessed through the comparison of the computed results with three experimental tests realized at our laboratory and using a 87.5% Hydrogen Peroxide/High-Density Polyethylene couple. Corresponding results lead to regression rate errors varying in a wide range (from 10

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Special Issue “Advances in Hybrid Rocket Technology and Related Analysis Methodologies”

Abstract: Hybrid rockets are chemical propulsion systems that, in the most common configuration, employ a liquid oxidizer (or gaseous in much rarer cases) and a solid fuel; the oxidizer, stored in tanks, is properly injected in the combustion chamber where the solid fuel grain is bonded [...]

Cited by 14 publications

References 18 publications

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

Special Issue “Hybrid Rocket (Volume II)”

Pseudo-Two-Dimensional Modeling and Validation of a Hybrid Rocket Combustion Chamber

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