飞行控制系统作为电动垂直起降（electric vertical take-off and landing，eVTOL）飞行器的关键机载系统，需要具备和民机同样的安全性。为了设计满足eVTOL飞行器需求的飞控系统架构，根据适航规章梳理了安全性要求，并基于安全性要求介绍了eVTOL飞行器飞控系统飞控计算机、传感器和作动器余度设计技术，设计了一种基于安全性考虑的eVTOL飞行器飞控系统架构；分析了eVTOL飞行器旋翼构型下的典型功能危险，并采用故障树进行了安全性分析。结果表明，设计的飞控系统架构的典型功能危险能够满足失效概率的要求。

The flight control system serves as the key airborne system for electric vertical takeoff and landing (eVTOL) aircraft, necessitating safety standards akin to those applied to civil aircraft. This study introduces redundancy design technology for the flight control computer, sensor and actuator in eVTOL aircraft flight control systems. It proceeds to design an architecture adhering to safety requirements in accordance with airworthiness regulations. The rotor configuration of eVTOL aircraft is considered, and typical functional hazards are analyzed. Safety analysis is carried out using fault tree analysis technology. The results show that the flight control system architecture designed in this study can effectively address the typical functional hazards, meeting the stipulated failure probability requirements.

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国家自然科学基金资助项目（U19A2060）。