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http://dx.doi.org/10.6108/KSPE.2019.23.3.119

Investigation on Chilling Procedure for LOX Supply System for Liquid Rocket Engine  

Cho, Nam-Kyung (Engine Test & Evaluation Team, Korea Aerospace Research Institute)
Seo, Dae-Bahn (Engine Test & Evaluation Team, Korea Aerospace Research Institute)
Yoo, Byung-Il (Engine Test & Evaluation Team, Korea Aerospace Research Institute)
Kim, Seong-Han (Engine Test & Evaluation Team, Korea Aerospace Research Institute)
Han, Yeoung-Min (Engine Test & Evaluation Team, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.23, no.3, 2019 , pp. 119-126 More about this Journal
Abstract
For rockets using cryogenic liquid hydrogen or liquid oxygen, chilling is required to avoid cavitation and surge problems. Chilling is categorized by the initial chilling/filling stage and the low-temperature maintenance stage. In addition, to improve satellite insertion capability, a multi-ignition capability is required and accordingly chilling to prepare for the next ignition during low-gravity coasting is also required. This paper describes the overall aspects of filling and low temperature maintain marinating for the booster and the upper stage engine including chilling for multi-ignition.
Keywords
Chilling; Cryogenic; LOX; Re-circulation; Drain; Filling stage; Cavitation; Multi-ignition;
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