Method for determining nozzle-throat-erosion history in hybrid rockets

Landon Kamps; Yuji Saito; Ryosuke Kawabata; Masashi Wakita; Tsuyoshi Totani; Yusuke Takahashi; Harunori Nagata

doi:10.2514/1.B36390

Method for determining nozzle-throat-erosion history in hybrid rockets

Landon Kamps, Yuji Saito, Ryosuke Kawabata, Masashi Wakita, Tsuyoshi Totani, Yusuke Takahashi, Harunori Nagata

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Abstract

The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flowrates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.

Original language	English
Pages (from-to)	1369-1377
Number of pages	9
Journal	Journal of Propulsion and Power
Volume	33
Issue number	6
DOIs	https://doi.org/10.2514/1.B36390
Publication status	Published - 2017

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10.2514/1.B36390

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title = "Method for determining nozzle-throat-erosion history in hybrid rockets",

abstract = "The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flowrates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.",

author = "Landon Kamps and Yuji Saito and Ryosuke Kawabata and Masashi Wakita and Tsuyoshi Totani and Yusuke Takahashi and Harunori Nagata",

note = "Funding Information: The authors would like to thank Tsutomu Uematsu and the staff at Uematsu Electric Co., Ltd. for their hard work and support in carrying out the static-firing tests conducted for this study. This research is supported by the Ministry of Education, Science, Sports and Culture, Grant-in-Aid for Science Research (B). 15H04197, 2016. Publisher Copyright: Copyright {\textcopyright} 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.",

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doi = "10.2514/1.B36390",

language = "English",

volume = "33",

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AU - Kamps, Landon

AU - Saito, Yuji

AU - Kawabata, Ryosuke

AU - Wakita, Masashi

AU - Totani, Tsuyoshi

AU - Takahashi, Yusuke

AU - Nagata, Harunori

N1 - Funding Information: The authors would like to thank Tsutomu Uematsu and the staff at Uematsu Electric Co., Ltd. for their hard work and support in carrying out the static-firing tests conducted for this study. This research is supported by the Ministry of Education, Science, Sports and Culture, Grant-in-Aid for Science Research (B). 15H04197, 2016. Publisher Copyright: Copyright © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

PY - 2017

Y1 - 2017

N2 - The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flowrates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.

AB - The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flowrates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.

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Method for determining nozzle-throat-erosion history in hybrid rockets

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