行星软着陆、采样返回等深空探测任务对推进系统深度变推力能力提出了严苛要求，电动泵压式火箭发动机凭借结构简单、控制解耦等优势而备受关注。本文针对电动泵压式发动机的推力调节问题，提出基于永磁同步电机矢量控制的最优扭矩调节方案，通过引入制动扭矩与加速扭矩的前馈干预，实现推力降低与增加过程的快速响应。通过建立电动泵压式火箭发动机系统动力学模型，并结合多工况仿真，分析了不同电机扭矩方案对推力调节时间的影响，结果表明，最优扭矩调节可将推力降低过程时间缩短74%-86%，推力增加过程时间缩短45%-75%。此外，燃料电机在推力调节中的主导作用显著，而液氧电机调节速度较快，其干预效果有限。工况敏感性分析表明，发动机推力水平越低、推力调节深度越大或设定的干预时间越短，电机需要承受的扭矩负担就越重。综合考虑电机自身扭矩范围的物理限制，本研究提出的最优扭矩调节方案更适用于发动机的多级深度推力调节任务。
Deep space exploration missions such as planetary soft landing and sample return impose strict requirements on the deep throttling capability of propulsion systems. Electric pump-fed rocket engines have attracted significant attention due to their advantages including simple structures and decoupled control. Addressing the thrust regulation problem of electric pump-fed engines, this paper proposes an optimal torque regulation scheme based on the vector control of permanent magnet synchronous motors. This scheme achieves rapid responses during thrust reduction and increase processes through the feedforward intervention of braking and accelerating torques. A system dynamics model for the electric pump-fed rocket engine is established, and combined with multi-condition simulations, the impact of different motor torque schemes on thrust regulation time is analyzed. Results show that optimal torque regulation reduces the thrust reduction time by 74% to 86% and the thrust increase time by 45% to 75%. Furthermore, the fuel motor plays a dominant role in thrust regulation, whereas the liquid oxygen motor regulates faster, resulting in limited intervention effects. Operating condition sensitivity analysis demonstrates that lower engine thrust levels, greater thrust regulation depths, or shorter set intervention times impose heavier torque burdens on the motor. Considering the physical limits of the inherent torque range of the motor, the optimal torque regulation scheme proposed in this study is more suitable for multi-stage deep throttling tasks in rocket engines.
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