Proof-of-Concept Testing of a Sustained Vortex-Flow Configuration for Hybrid Rocket Motors

R. Wilkinson, R. Day, K. Hart

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

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    Abstract

    One 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.
    Original languageEnglish
    Title of host publicationProcs 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf & Exhibit
    PublisherAIAA
    Volume2010
    Publication statusPublished - 2010
    Event46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf & Exhibit - Nashville, United States
    Duration: 25 Jul 201028 Jul 2010

    Conference

    Conference46th AIAA/ASME/SAE/ASEE Joint Propulsion Conf & Exhibit
    Country/TerritoryUnited States
    CityNashville
    Period25/07/1028/07/10

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