Theoretical and experimental study of combustion instability in hybrid rocket motors

Bertoldi, Artur Elias de Morais; Bouziane, Mohammed; Lee, Jungpyo; Veras, Carlos Alberto Gurgel; Hendrick, Patrick; Simone, Domenico

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Campo DC	Valor	Idioma
dc.contributor.author	Bertoldi, Artur Elias de Morais	-
dc.contributor.author	Bouziane, Mohammed	-
dc.contributor.author	Lee, Jungpyo	-
dc.contributor.author	Veras, Carlos Alberto Gurgel	-
dc.contributor.author	Hendrick, Patrick	-
dc.contributor.author	Simone, Domenico	-
dc.date.accessioned	2019-12-02T12:46:36Z	-
dc.date.available	2019-12-02T12:46:36Z	-
dc.date.issued	2019	-
dc.identifier.citation	BERTOLDI, Artur Elias de Morais et al. Theoretical and experimental study of combustion instability in hybrid rocket motors. In: EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS), 8., 2019, Madri. Proceedings [...]. Madrid: EUCASS association, 2019. DOI: 10.13009/EUCASS2019-538. Disponível em: https://www.eucass.eu/index.php/conferences-and-publications/search-in-publications?searchword=eucass/2019&searchphrase=all&limit=20&areas[0]=doc_indexer&start=280. Acesso em: 02 dez. 2019.	pt_BR
dc.identifier.uri	https://repositorio.unb.br/handle/10482/35908	-
dc.language.iso	Inglês	pt_BR
dc.publisher	EUCASS association	pt_BR
dc.rights	Acesso Restrito	pt_BR
dc.title	Theoretical and experimental study of combustion instability in hybrid rocket motors	pt_BR
dc.type	Trabalho	pt_BR
dc.subject.keyword	Motores de foguetes	pt_BR
dc.subject.keyword	Câmaras de combustão	pt_BR
dc.rightsholder	Copyright © 2019 by A.E.M Bertoldi, M. Bouziane, J. Lee, C.A.G. Veras, P. Hendrick and D. Simone . Published by the EUCASS association with permission.	-
dc.identifier.doi	10.13009/EUCASS2019-538	pt_BR
dc.relation.publisherversion	https://www.eucass.eu/index.php/conferences-and-publications/search-in-publications?searchword=eucass/2019&searchphrase=all&limit=20&areas[0]=doc_indexer&start=280	pt_BR
dc.description.abstract1	This work describes a theoretical and experimental study of combustion instability in hybrid rocket motors. Results are highlighting that the parameter Δ𝑝 /𝑝̅c (pressure drop between tank and chamber scaled by average chamber pressure) plays an important role in the oscillatory characteristics of the chamber pressure. By modifying the feed-system-coupled instability theory, a combustion time lag model has been developed; using this a new general analysis criterion is proposed. Results show good agreement with the experimental data and suggest that the combustion time delay of the liquid oxidizer is more important than the response time of solid fuel boundary layer.	pt_BR
dc.description.unidade	Faculdade UnB Gama (FGA)	-
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