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dc.contributor.authorWilkinson, R.
dc.contributor.authorDay, R.
dc.contributor.authorHart, K.
dc.date.accessioned2011-11-10T13:01:05Z
dc.date.available2011-11-10T13:01:05Z
dc.date.issued2010
dc.identifier.citationWilkinson , R , Day , R & Hart , K 2010 , Proof-of-Concept Testing of a Sustained Vortex-Flow Configuration for Hybrid Rocket Motors . in Procs 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf & Exhibit . vol. 2010 , AIAA , 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf & Exhibit , Nashville , United States , 25/07/10 .
dc.identifier.citationconference
dc.identifier.otherPURE: 447566
dc.identifier.otherPURE UUID: c81dbbe8-9981-44e5-ad6d-7f790fd3b7a0
dc.identifier.otherdspace: 2299/4704
dc.identifier.urihttp://hdl.handle.net/2299/6975
dc.descriptionCopyright © 2010 by University of Hertfordshire and Eur Ing R Wilkinson. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
dc.description.abstractOne of the drawbacks of hybrid rocket motors is the limited regression rate of the fuel grain, which impacts on the scalablility of the type. A number of methods of increasing this have been proposed and successfully tested, in particular the use of swirling oxidiser flow to create turbulence and increase the local oxidiser mass flux. However, many of these have limitations in practical motors for many applications, and a common problem is that of the swirl decaying within the motor. The proposed method described here is to use a tapering fuel-grain port to sustain the swirl. A short series of firings indicates that such a method may be effective, although the evidence is limited thus far. The majority of previous research has used gaseous oxygen, and it has been found during this test programme that using liquid nitrous oxide poses particular problems. However, solutions have been found, and are described in this paper.en
dc.language.isoeng
dc.publisherAIAA
dc.relation.ispartofProcs 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf & Exhibit
dc.rightsOpen
dc.titleProof-of-Concept Testing of a Sustained Vortex-Flow Configuration for Hybrid Rocket Motorsen
dc.contributor.institutionSchool of Engineering and Technology
dc.relation.schoolSchool of Engineering and Technology
dc.description.versiontypeFinal Published version
dcterms.dateAccepted2010
rioxxterms.versionVoR
rioxxterms.typeOther
herts.preservation.rarelyaccessedtrue
herts.rights.accesstypeOpen


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