HTPB hybrid propulsion with multiple vortical-flow chamber designs

Yen Sen Chen*, Alfred Lai, Jhe Wei Lin, Tzu Hao Chou, Jong-Shinn Wu

*Corresponding author for this work

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

7 Scopus citations

Abstract

One main physical feature of hybrid rocket combustion is its diffusion flame nature that has required excessively long combustion chamber which leads to undesirable large slenderness of a rocket configuration. The diffusion flame also results in generally low combustion efficiency of hybrid rockets. Some remedial designs have used liquefying solid grain, such as paraffin, or mixing enhancement mechanisms to boost the overall fuel regression rate and combustion efficiency. Thus, shortened combustion chambers can be used to deliver reasonable thrust performance of hybrid rockets. In the present study, a compact hybrid rocket motor design is investigated to provide a form factor with small slenderness, which is suitable for improving the overall system designs for hybrid rockets. This design concept features in multiple vortical flow structures such that much enhanced combustion efficiency can be obtained. A 3-D computational model with finite-rate chemistry using reduced kinetics mechanism and radiative heat transfer effects are employed in the present investigation to assess the mixing effectiveness and combustion efficiency of the present design. This computational model has been validated for a wide range of rocket propulsion design problems, including single-port hybrid rocket motors with mixing enhancement vortex generator devices. The internal ballistics and flame structure in the present multiple vortical-flow hybrid rocket engine designs using HTPB fuel with nitrous oxide or hydrogen peroxide oxidizers are investigated.

Original languageEnglish
Title of host publication50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624103032
DOIs
StatePublished - 1 Jan 2014
Event50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States
Duration: 28 Jul 201430 Jul 2014

Publication series

Name50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014

Conference

Conference50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
CountryUnited States
CityCleveland
Period28/07/1430/07/14

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  • Cite this

    Chen, Y. S., Lai, A., Lin, J. W., Chou, T. H., & Wu, J-S. (2014). HTPB hybrid propulsion with multiple vortical-flow chamber designs. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2014-3544