University of Hertfordshire

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

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

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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
CountryUnited States
CityNashville
Period25/07/1028/07/10

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.

Notes

Copyright © 2010 by University of Hertfordshire and Eur Ing R Wilkinson. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.

ID: 447566