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dc.contributor.authorChen Yen-Senen_US
dc.contributor.authorWu Men-Zenen_US
dc.contributor.authorWu Jong-Shinnen_US
dc.contributor.authorLai Alfreden_US
dc.contributor.authorLin Jhe-Weien_US
dc.contributor.authorChou Tzu-Haoen_US
dc.date.accessioned2014-12-16T06:14:41Z-
dc.date.available2014-12-16T06:14:41Z-
dc.date.issued2014-12-04en_US
dc.identifier.govdocF02K009/00zh_TW
dc.identifier.urihttp://hdl.handle.net/11536/104854-
dc.description.abstractThe present invention discloses a dual-vortical-flow hybrid rocket engine, including a main body and a nozzle communicating with an end of the main body. The main body includes a plurality of disk-like combustion chambers arranged longitudinally, and a central combustion chamber formed along the axial portion and communicating the disk-like combustion chambers. Each of the disk-like combustion chambers is provided with a plurality of oxidizer injection nozzles at its inner circumference surface. Inside the disk-like combustion chambers, the oxidizer is injected in nearly the tangent directions of the circumference, and the injection directions are opposite for the neighboring disk-like combustion chambers, which creates vortical flows with opposite rotating directions so as to increase the total residence time of the combustion reactions of the oxidizer and the solid-state fuel in the disk-like combustion chambers of the present invention.zh_TW
dc.language.isozh_TWen_US
dc.titleDual-Vortical-Flow Hybrid Rocket Enginezh_TW
dc.typePatentsen_US
dc.citation.patentcountryUSAzh_TW
dc.citation.patentnumber20140352276zh_TW
Appears in Collections:Patents


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