Advances in aircraft and spacecraft science

  • 제4권1호
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  • Pages.21-35
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  • 2017
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Liquid phase hydrogen peroxide decomposition for micro-propulsion applications

  • McDevitt, M. Ryan (Department of Mechanical Engineering, University of Vermont) ;
  • Hitt, Darren L. (Department of Mechanical Engineering, University of Vermont)
  • 투고 : 2016.02.26
  • 심사 : 2016.04.21
  • 발행 : 2017.01.25
⟨ 이전 논문 다음 논문 ⟩

초록

Hydrogen peroxide is being considered as a monopropellant in micropropulsion systems for the next generation of miniaturized satellites ('nanosats') due to its high energy density, modest specific impulse and green characteristics. Efforts at the University of Vermont have focused on the development of a MEMS-based microthruster that uses a novel slug flow monopropellant injection scheme to generate thrust and impulse-bits commensurate with the intended micropropulsion application. The present study is a computational effort to investigate the initial decomposition of the monopropellant as it enters the catalytic chamber, and to compare the impact of the monopropellant injection scheme on decomposition performance. Two-dimensional numerical studies of the monopropellant in microchannel geometries have been developed and used to characterize the performance of the monopropellant before vaporization occurs. The results of these studies show that monopropellant in the lamellar flow regime, which lacks a non-diffusive mixing mechanism, does not decompose at a rate that is suitable for the microthruster dimensions. In contrast, monopropellant in the slug flow regime decomposes 57% faster than lamellar flow for a given length, indicating that the monopropellant injection scheme has potential benefits for the performance of the microthruster.

키워드

과제정보

연구 과제 주관 기관 : NASA

참고문헌

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