Solid fuel regression measurements rate using an optical hybrid rocket engine

Dillon J. Over, Makayla L.L. Ianuzzi, Jeffrey D. Moore, Grant Alexander Risha

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

2 Scopus citations

Abstract

The focus of this research work was to develop an optical hybrid rocket engine that regression rates, various flame characteristics, and other chamber characteristics can be measured using conventional cinematography. For the current experimental series, hydroxyl-terminated polybutadiene (HTPB) or nylon PA66 fuels and gaseous oxygen were the reactants. Images of both the plume and the chamber interior were ascertained since the chamber was equipped with quartz and Plexiglas windows at capture rates from 2000 to 4000 frames per second. From the fourteen experimental test fires, the quartz windows were used for five tests and sustained the combustion event while maintaining a steady-state pressure of approximately 1.0 to 3.5 MPa. The gaseous oxygen was delivered at mass flow rates of 35 to 75 g/s and the thrust levels produced were 130 to 300 N.

Original languageEnglish (US)
Title of host publicationAIAA Propulsion and Energy Forum and Exposition, 2019
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105906
DOIs
StatePublished - 2019
EventAIAA Propulsion and Energy Forum and Exposition, 2019 - Indianapolis, United States
Duration: Aug 19 2019Aug 22 2019

Publication series

NameAIAA Propulsion and Energy Forum and Exposition, 2019

Conference

ConferenceAIAA Propulsion and Energy Forum and Exposition, 2019
CountryUnited States
CityIndianapolis
Period8/19/198/22/19

All Science Journal Classification (ASJC) codes

  • Energy(all)
  • Aerospace Engineering
  • Electrical and Electronic Engineering
  • Control and Systems Engineering
  • Mechanical Engineering

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