为解决小尺寸单人旋翼飞行器的飞行稳定性问题，针对整机尺寸小、载重大的特点，提出增稳结构方案，建立动力学模型并进行了模态仿真分析。首先，确定了飞行器的重心位置，确保设计满足飞行稳定性要求。其次，针对摇摆、振动等稳定性问题，提出了增稳结构方案。最后，通过不同阻尼器阻尼值的驾驶舱动力学仿真，确定了阻尼器方案，并完成了模态仿真分析。研究结果表明，研究的目标飞行器在保持小尺寸的同时，通过合理的结构设计和飞行控制策略，能够实现稳定飞行，满足实际应用需求。

In order to solve the flight stability issue of small-sized single-person rotorcraft，considering the small-sized and heavy load of the entire aircraft，a stability-enhancing structure scheme was proposed and modal simulation analysis was conducted. Firstly，the center of gravity was determined to ensure that the design met the requirements of flight stability.Secondly， a stability-enhancing structure scheme was proposed to address stability issues such as sway and vibration.Finally，the damper scheme was determined through cockpit dynamics simulation with different damping values of damper and the mode simulation analysis was completed.The results show that the target aircraft can achieve stable flight and meet the practical application requirements through reasonable structural design and flight control strategies while maintaining a small size.