电动泵压式液体火箭发动机具备系统架构简单、推力调节灵活等独特优势，能够满足当前航天任务的多样化需求，受到了领域内的广泛关注。作为一种新颖的循环方式，其启动过程的动态特性对发动机性能的影响规律具有重要的研究意义，因此本文基于双电机驱动的电动泵压式火箭发动机方案，设计了“箱压下先点火后爬升”和“先爬升再点火”两种点火时序，构建了电动泵压式火箭发动机的仿真模型，并对发动机启动过程的动态特性展开了研究。结果表明，两种启动方案下的发动机启动过程均出现了压力和混合比的波动，这是由于甲烷在冷却夹套内发生了相态变化所导致的，通过对比可知，“箱压下先点火后爬升”启动时序下发动机启动过程工况更为稳定，点火过程简单，“先爬升再点火”启动时序下发动机启动过程爬升速度更快。
The electric pump-fed liquid rocket engine boasts unique advantages including a simplified system architecture and flexible thrust modulation, enabling it to satisfy the diverse demands of modern aerospace missions and garnering widespread attention within the field. As an innovative cycle configuration, the impact of its start-up transient dynamics on engine performance represents a subject of significant research value. To this end, this paper takes a dual-motor-driven electric pump-fed rocket engine concept as its foundation, designing two distinct ignition sequences—“ignition first followed by thrust ramp-up under tank pressure” and “thrust ramp-up first then ignition”—and developing a dedi-cated simulation model for the engine. Building on this model, an in-depth investigation into the dynamic behaviors of the engine’s start-up phase is conducted.The results indicate that both start-up schemes give rise to fluctuations in pressure and mixture ratio, a phenomenon attributed to the phase transition of methane within the cooling jacket. A comparative analysis reveals that the “ignition first then ramp-up under tank pressure” sequence yields more stable operating conditions during start-up alongside a streamlined ignition process. Conversely, the “ramp-up first then igni-tion” sequence delivers a considerably faster thrust ramp-up rate during the engine’s start-up phase.
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