Method for determining nozzle throat erosion history in hybrid rockets

Landon Kamps, Yuji Saito, Ryosuke Kawabata, Yusuke Takahashi, Harunori Nagata

研究成果: Conference contribution

1 被引用数 (Scopus)

抄録

The authors introduce a new reconstruction technique titled Nozzle Throat Reconstruction Technique or NTRT to estimate nozzle throat erosion history and oxidizerto-fuel mass ratio history in hybrid rockets. Nine five-second 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 NTRT results. Nozzle throat erosion histories calculated by NTRT agreed well with measured values for initial and final nozzle throat radius, and successfully reconstructed the case where no measureable amount of nozzle throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle throat erosion rate and equivalence ratio determined by NTRT displays a trend consistent with chemical kinetic limited heterogeneous combustion theory, as well as predictions made by previous researchers. A numerical simulation was carried out to investigate the applicability of an alternative computational technique which uses a nozzle exit pressure measurement as input data, and revealed that pressure in vicinity of the static pressure port is likely to deviate from centerline pressure by up to 0.1 [MPa] or 30%.

本文言語English
ホスト出版物のタイトル52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624104060
DOI
出版ステータスPublished - 2016
外部発表はい
イベント52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016 - Salt Lake City, United States
継続期間: 2016 7 252016 7 27

出版物シリーズ

名前52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016

Conference

Conference52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
CountryUnited States
CitySalt Lake City
Period16/7/2516/7/27

ASJC Scopus subject areas

  • Engineering(all)

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