Orbital Maneuver Study of High-Low Thrust Combined Multimodal Water Propulsion for On-Orbit Servicing 高低推力组合多模态水推进在轨服务轨道机动研究
- 针对400 km LEO轨道、180°大相位差交会任务中时间与燃料消耗的矛盾，利用修正赤道根数（MEE）构建高保真绝对轨道动力学模型，并针对纯高推力、纯低推力及高低推力复合策略设定统一对比口径，为终端距离误差控制在100m以内的轨迹优化提供了可复现的仿真评估基准。
- 针对推力模式切换纹波导致轨道积分污染与终端误差失真的问题，在仿真中设计PID切换控制逻辑将推力波动抑制在±5%以内，并深度集成Lambert算法与庞特里亚金最小值原理（PMP）进行轨迹精确求解，实现了对燃料消耗、速度增量及任务指标的自动化汇总与高信度评估。
- 为验证多模态水推进系统在在轨服务中的性能优势，在匹配初始与终端约束条件下完成三类机动策略对比，复合策略较纯高推力方案节燃达73.1%，较燃料最优低推力方案缩短任务时间12.5%（仅需84小时），在实现性能最优平衡的同时通过双模冗余设计显著提升了任务可靠性。
摘要
Aiming at the contradictory requirements of rapid large-scale orbital transfer and high-precision fuel-efficient orbit control in on-orbit servicing (OOS) missions, this paper proposes a multimodal water-propellant propulsion system integrating hydrogen-oxygen combustion high-thrust mode and electromagnetic plasma low-thrust mode. Three orbital maneuver strategies for a 180° phase-difference long-range rendezvous mission in 400 km LEO are designed: pure high-thrust impulsive, pure low-thrust optimal, and high-low thrust combined. High-fidelity simulations are carried out using the Lambert algorithm and Pontryagin’s minimum principle. Results show the combined strategy reduces fuel consumption by 73.1% compared to pure high-thrust, and shortens mission time by 12.5% compared to fuel-optimal low-thrust, while dual-mode redundancy improves mission reliability.