CN CN122540370A
本发明属于飞行器技术领域，具体涉及仿生扑翼飞行器，尤其涉及一种高压流体助力的扑翼飞行系统及控制方法，旨在解决现有纯扑翼飞行器载荷不足难以适配载人需求、现有旋翼载人飞行器外露高速运动部件安全风险高的问题。所述扑翼飞行系统核心包括控制系统、高压流体助力系统、扑翼机构与机身；高压流体助力系统以集成动力单元的舵船为承载基体，可输出高压水或高压空气并通过喷流装置定向喷射产生反推力或调控翼面流场，与扑翼机构的气动升力协同匹配全飞行阶段的动力需求。本发明无需增设外露高速运动部件，即可显著提升整机升推力、降低扑翼结构载荷，具备载荷能力强、起降距离短、安全性高、运维成本低的优势，本系统可适配有尾/无尾、带/不带起落架等多种整机构型，适用于近水面短途载人通勤、休闲飞行等场景，兼顾通行效率与仿生飞行体验。
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