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 LOX/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.

中文翻译：

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O/F 比对具有 ElecPump-fed 循环的低推力 LOX/甲烷火箭发动机性能的影响

最近，电动泵送循环火箭发动机（即ElecPump 发动机）受到了相当大的关注。ElecPump 发动机优于压力供给发动机，并且可能会在 100 kN 推力水平下取代气体发生器循环发动机。本研究侧重于低推力水平的 LOX/甲烷 ElecPump 发动机，并估计发动机的标称运行点。目标变量设置为舞台的最大速度增量。混合比和燃烧压力被探索为设计变量。因此，将最佳混合比作为设计变量提出，不仅要考虑发动机重量，还要考虑结构重量。