Design of hydrogen-electric extended-range hybrid power system for compound-wing UAVs
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摘要:
针对复合翼无人机（UVA）发展面临的悬停高能耗与长航时需求冲突问题，提出一种氢电增程式混合动力系统设计。为保证巡航效率的同时提升悬停阶段能源利用效率，设计采用燃料电池为核心的高能量密度混合动力系统，优化传统复合翼无人机的能源系统布局结构。在此基础上，提出了一种面向跨模式飞行工况的氢电协同功率调度策略，动态分配燃料电池与锂电池的输出功率，在巡航阶段可将动力电池的荷电状态（SOC）稳定恢复并保持在95%的预设值，在保障高耗能悬停作业功率冗余的同时，实现氢-电协同输出的能量动态平衡与全局氢气消耗量最优。通过仿真试验与飞行验证，系统支持样机完成了28 min悬停与230 km巡航的复合任务，相较于rule-based equivalent consumption minimization strategy（RB-ECMS）策略，氢气消耗量降低了约8.3%，为复合翼无人机提供了一种高效清洁的混合动力解决方案。
Abstract:To resolve the conflict between high hover energy consumption and long endurance in compound-wing unmanned aerial vehicle (UAV), a high-energy-density hydrogen-electric extended-range hybrid power system is proposed. A cross-modal power scheduling strategy dynamically allocates output between the fuel cell and lithium battery, maintaining a 95% state of charge (SOC) during cruise to ensure hovering power redundancy and optimize global hydrogen consumption. Validated through simulations and flight tests, the prototype achieved a 28 min hover and a 230 km cruise. Notably, it reduced hydrogen consumption by approximately 8.3% compared to the rule-based equivalent consumption minimization strategy (RB-ECMS) strategy, providing an efficient and clean hybrid power solution.
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图 1 氢电增程式混合动力系统组成结构
Figure 1. Structure of hydrogen-electric extended-range hybrid power system
图 2 氢电增程式混合动力系统的复合翼无人机
Figure 2. Compound-wing UAV with hydrogen-electric extended-range hybrid power system
图 8 电池SOC、发电功率、阀门开度和电堆温度随时间的变化
Figure 8. Variation of battery SOC, generation power, valve opening and stack temperature with time
图 9 动推力和功率消耗随阀门开度的变化
Figure 9. Variation of dynamic thrust and power consumption with valve opening
图 12 全飞行剖面下不同能量管理策略的氢气消耗量演变轨迹
Figure 12. Hydrogen consumption evolution trajectories under different energy management strategies across the entire flight profile
图 13 氢电增程式混合动力多旋翼测试台架实物
Figure 13. Photograph of the hydrogen-electric extended-range hybrid multirotor test bench.
图 15 氢电增程式混合动力系统复合翼无人机样机
Figure 15. Prototype of the Hydrogen-Electric Extended-Range Hybrid Compound-Wing UAV
图 16 氢电增程式混合动力系统多模态飞行实测功率时序响应曲线
Figure 16. Measured power time-series response curves of the hydrogen-electric extended-range hybrid power system under multi-modal flight
图 17 多模态工况下氢电增程式无人机电池SOC动态响应特性
Figure 17. Dynamic Response Characteristics of Battery SOC for the Hydrogen-Electric Extended-Range UAV Under Multi-Modal Operating Conditions.
表 1 仿真飞行参数设定
Table 1. Simulation flight parameter settings
参数 数值 m/kg 35 v/（m/s） 25 P/W 2500 SOC/% 95 C/（mA·h） 12000 t1/s 120 t2/s 2300 t3/s 200 t4/s 2400 t5/s 300 t6/s 2500 t7/s 180 
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表 2 氢电复合翼无人机试飞参数
Table 2. Flight Test Parameters of the Hydrogen-Electric Compound-Wing UAV
参数 数值 m/kg 35 mmax/kg 38 V/（km/h） 90～100 b/m 3.92 l/m 2.36 P/W 2500 C/mAh 12000 SOC/% 95 vw/（m/s） 3 V-w/L 12
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