Inscrição na biblioteca: Guest
Portal Digital Begell Biblioteca digital da Begell eBooks Diários Referências e Anais Coleções de pesquisa
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Imprimir: 2150-766X
ISSN On-line: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v9.i4.20
pages 305-326

RECENT ADVANCES IN HYBRID PROPULSION

Brian Cantwell
Stanford University and Space Propulsion Group, Incorporated, Sunnyvale, California
Arif Karabeyoglu
Stanford University and Space Propulsion Group Inc., 39120 Argonaut Way, Fremont, California 94538, USA; Koç University, Rumeli Feneri Yolu, Sariyer, Istanbul, 34450, Turkey
David Altman
Stanford University and Space Propulsion Group, Incorporated, Sunnyvale, California

RESUMO

The idea of the hybrid rocket is to store the oxidizer as a liquid and the fuel as a solid, producing a design that minimizes the chance of a chemical explosion. While the hybrid enjoys many safety and environmental advantages over conventional systems, large hybrids have not been commercially viable. The reason is that traditional systems use polymeric fuels that evaporate too slowly, making it difficult to produce the high thrust needed for most applications. Research at Stanford University and Space Propulsion Group (SPG) has led to the development of paraffin-based fuels that burn at regression rates 3-4 times that of polymeric fuels. Under the action of the oxidizer flow, the new fuels form a thin, hydrodynamically unstable liquid layer on the melting surface of the fuel. Entrainment of droplets from the liquid-gas interface can substantially increase the rate of fuel mass transfer, leading to a much higher surface regression rate than can be achieved with a conventional fuel. To demonstrate the use of these fuels, a series of scale-up tests using several oxidizers has been carried out on intermediate-scale motors. The data from these tests are in agreement with small-scale, low- pressure, and low-mass-flux laboratory tests and confirm the high regression rate behavior of the fuels at chamber pressures and mass fluxes representative of commercial applications. Recently, SPG has developed a new class of oxidizers based on refrigerated mixtures of N2O and oxygen. The mixtures combine the high vapor pressure of dissolved oxygen with the high density of refrigerated N2O to produce a self-pressurizing oxidizer with high density and good performance. The combination of these technologies leads to a hybrid rocket design with reduced system size and mass.


Articles with similar content:

OBSERVATION OF COMBUSTION BEHAVIOR OF LOW MELTING TEMPERATURE FUEL FOR A HYBRID ROCKET USING DOUBLE SLAB MOTOR
International Journal of Energetic Materials and Chemical Propulsion, Vol.15, 2016, issue 5
Ryuichi Kato, Yo Kawabata, Nobuji Kato, Keiichi Hori, Yutaka Wada
INSENSITIVE HIGH ENERGY BOOSTER PROPELLANT SUITABLE FOR HIGH PRESSURE OPERATION
International Journal of Energetic Materials and Chemical Propulsion, Vol.6, 2007, issue 4
Alan D. Turner, May Lee Chan
ENVIRONMENT-FRIENDLY COMPOSITE PROPELLANTS BASED ON AMMONIUM DINITRAMIDE
International Journal of Energetic Materials and Chemical Propulsion, Vol.18, 2019, issue 1
Claudio Tagliabue, Volker Weiser, Volker Gettwert, Sven Hafner, Sebastian Fischer
PROPULSION AND CATALYSIS − HISTORICAL SURVEY, UP-TO-DATE OVERVIEW, AND CURRENT CHALLENGES
International Journal of Energetic Materials and Chemical Propulsion, Vol.9, 2010, issue 5
Laurence Pirault-Roy, Yann Batonneau, Charles J. Kappenstein, Rachid Brahmi
NEW ENERGETIC MATERIALS FOR THE PROPULSION OF SPACE VEHICLES AND ROCKETS
International Journal of Energetic Materials and Chemical Propulsion, Vol.7, 2008, issue 3
Haridwar Singh, S. P. Tiwari