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International Journal of Energetic Materials and Chemical Propulsion

Published 6 issues per year

ISSN Print: 2150-766X

ISSN Online: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

Indexed in

CHALLENGES IN THE DEVELOPMENT OF LARGE-SCALE HYBRID ROCKETS

Volume 16, Issue 3, 2017, pp. 243-261
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2018022732
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ABSTRACT

Advanced hybrid rockets, which combine fast burning fuels, composite motor construction, and innovative internal ballistic design, have the capability to deliver high performance while retaining the cost, environmental, and simplicity advantages of the classical hybrids. This makes hybrid rocket propulsion a tipping point technology in the sense that a small, short-term investment could have game-changing consequences in the development of green, safe, affordable, and high-performance systems needed for future space missions. In order to demonstrate the advantages of hybrids most effectively, the effort should be concentrated on improving the technology readiness level of the technology for a carefully selected class of missions. That being said, some serious challenges still exist in the development of operational motors, even for applications highly suitable for hybrid propulsion. These challenges, some perceived whereas others are very real, are carefully outlined in this paper. The real-life importance of each challenge is also discussed, along with potential methods to mitigate these issues. The ultimate strategy in the elimination of any practical challenge is that the solution should not compromise the simplicity, cost, and safety advantages of classical hybrid rockets. The solution methodology should be an iterative process that involves a well-balanced combination of theoretical modeling, numerical simulations, and actual motor testing. Advanced hybrid rockets, which combine fast burning fuels, composite motor construction, and innovative internal ballistic design, have the capability to deliver high performance while retaining the cost, environmental, and simplicity advantages of the classical hybrids. This makes hybrid rocket propulsion a tipping point technology in the sense that a small, short-term investment could have game-changing consequences in the development of green, safe, affordable, and high-performance systems needed for future space missions. In order to demonstrate the advantages of hybrids most effectively, the effort should be concentrated on improving the technology readiness level of the technology for a carefully selected class of missions. That being said, some serious challenges still exist in the development of operational motors, even for applications highly suitable for hybrid propulsion. These challenges, some perceived whereas others are very real, are carefully outlined in this paper. The real-life importance of each challenge is also discussed, along with potential methods to mitigate these issues. The ultimate strategy in the elimination of any practical challenge is that the solution should not compromise the simplicity, cost, and safety advantages of classical hybrid rockets. The solution methodology should be an iterative process that involves a well-balanced combination of theoretical modeling, numerical simulations, and actual motor testing.

CITED BY
  1. Bendana Fabio A., Castillo Josue J., Hagström China G., Spearrin Raymond M., Thermochemical structure of a hybrid rocket reaction layer based on laser absorption tomography, AIAA Propulsion and Energy 2019 Forum, 2019. Crossref

  2. Quadros Flávio D. A., Lacava Pedro T., Swirl Injection of Gaseous Oxygen in a Lab-Scale Paraffin Hybrid Rocket Motor, Journal of Propulsion and Power, 35, 5, 2019. Crossref

  3. Paccagnella Enrico, Santi Marco, Ruffin Alessandro, Barato Francesco, Pavarin Daniele, Misté Gianluigi A., Venturelli Giovanni, Bellomo Nicolas, Testing of a Long-Burning-Time Paraffin-Based Hybrid Rocket Motor, Journal of Propulsion and Power, 35, 2, 2019. Crossref

  4. Sanders Isabelle C., Bendana Fabio A., Hagstrom China, Spearrin Raymond M., Assessing Oxidizer Injector Design via Thermochemical Imaging of PMMA Combustion in a Hybrid Rocket Motor Geometry, AIAA Propulsion and Energy 2020 Forum, 2020. Crossref

  5. Bendana Fabio A., Sanders Isabelle C., Castillo Josue J., Hagström China G., Pineda Daniel I., Spearrin R. Mitchell, In-situ thermochemical analysis of hybrid rocket fuel oxidation via laser absorption tomography of $$\text {CO}$$, $$\text {CO}_{2}$$, and $$\text {H}_{2}\text {O}$$, Experiments in Fluids, 61, 9, 2020. Crossref

  6. Okninski Adam, Surmacz Pawel, Bartkowiak Bartosz, Mayer Tobiasz, Sobczak Kamil, Pakosz Michal, Kaniewski Damian, Matyszewski Jan, Rarata Grzegorz, Wolanski Piotr, Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer, Aerospace, 8, 9, 2021. Crossref

  7. Sanders Isabelle C., Bendana Fabio A., Hagström China G., Mitchell Spearrin R., Injector Effects on Hybrid Polymethylmethacrylate Combustion Assessed by Thermochemical Tomography, Journal of Propulsion and Power, 37, 6, 2021. Crossref

  8. Sanders Isabelle C., Bendana Fabio A., Stacy Nora, Schwarm Kevin K., Spearrin R. Mitchell, Swirl injection in hybrid polymethylmethacrylate combustion assessed by thermochemical imaging, AIAA Propulsion and Energy 2021 Forum, 2021. Crossref

  9. Kuenning Nicholas, Sanders Isabelle C., Mellor Tara, Minesi Nicolas Q., Pineda Daniel I., Spearrin Raymond M., Kinetics of methyl methacrylate (MMA) combustion assessed by time-resolved speciation behind shock waves, AIAA SCITECH 2022 Forum, 2022. Crossref

  10. Sanders Isabelle C., Bendana Fabio A., Kuenning Nicholas, Spearrin Raymond M., Spatially-resolved characteristic velocity (c*) measurements for hybrid rocket combustion analysis using laser spectroscopy, AIAA SCITECH 2022 Forum, 2022. Crossref

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