Effects of the O/F Ratio on the Performance of a Low Thrust LOX/Methane Rocket Engine with an ElecPump-fed Cycle

Recently, electrically driven pump-fed cycle rocket engines (i.e., ElecPump engines) have received considerable attention. ElecPump engines are superior to pressure-fed engines and will likely replace gas generator cycle engines under a 100 kN thrust level. This study focuses on LO X /methane ElecPu...

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Bibliographic Details
Published inInternational journal of aeronautical and space sciences Vol. 21; no. 4; pp. 1037 - 1046
Main Authors Yu, Byungil, Kwak, Hyun-Duck, Kim, Hong Jip
Format Journal Article
LanguageEnglish
Published Seoul The Korean Society for Aeronautical & Space Sciences (KSAS) 01.12.2020
한국항공우주학회
Subjects
Aerospace Technology and Astronautics
Engineering
Fluid- and Aerodynamics
Original Paper
항공우주공학
Electric propulsion
Liquid rocket engine
Liquid methane
Specific impulse
Liquid oxygen
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Summary:Recently, electrically driven pump-fed cycle rocket engines (i.e., ElecPump engines) have received considerable attention. ElecPump engines are superior to pressure-fed engines and will likely replace gas generator cycle engines under a 100 kN thrust level. This study focuses on LO X /methane ElecPump engines with a low-thrust level and estimates the nominal operation point of the engine. The objective variable was set to the maximum velocity increment of the stage. The mixture ratio and combustion pressure were explored as the design variables. Thus, the optimal mixture ratio was proposed as the design variable, considering not only the engine weight but also the structural weight.
Bibliography:https://link.springer.com/article/10.1007/s42405-020-00318-y
ISSN:2093-274X
2093-2480
DOI:10.1007/s42405-020-00318-y