Orbital Maneuver Study of High-Low Thrust Combined Multimodal Water Propulsion for On-Orbit Servicing 高低推力組合多模態水推進在軌服務軌道機動研究
- 針對400 km LEO軌道、180°大相位差交會任務中時間與燃料消耗的矛盾，利用修正赤道根數（MEE）建構高保真絕對軌道動力學模型，並針對純高推力、純低推力及高低推力複合策略設定統一對比口徑，為終端距離誤差控制在100m以內的軌跡最佳化提供了可重現的模擬評估基準。
- 針對推力模式切換紋波導致軌道積分污染與終端誤差失真之問題，於模擬中設計 PID 切換控制邏輯將推力波動抑制在 ±5% 以內，並深度整合 Lambert 演算法與龐特里亞金最小值原理（PMP）進行軌跡精確求解，實現了對燃料消耗、速度增量及任務指標之自動化彙總與高信度評估。
- 為驗證多模態水推進系統於在軌服務中之性能優勢，於匹配初始與終端約束條件下完成三類機動策略對比，複合策略較純高推力方案節燃達73.1%，較燃料最優低推力方案縮短任務時間12.5%（僅需84小時），於實現性能最優平衡之同時透過雙模冗餘設計顯著提升了任務可靠性。
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.