翼尖铰接组合式无人机是一类新概念飞行器，其由多个单体无人机以翼尖铰接形式连接而成并允许相对滚转运动，在布局参数及飞行力学特性上与常规飞行器有较大不同，单体无人机间存在气动耦合。首先基于状态空间形式涡格法给出了针对该类型飞行器的气动导数计算方法。然后，结合Newton-Euler方程建立的飞行力学模型进行配平计算及飞行力学稳定性分析，说明其具有以相对滚转运动主导的不稳定复合运动飞行模态特征。最后，开展布局参数对飞行动力学稳定性影响研究，经分析，减小单体无人机配平滚转角，增加后掠角可以改善飞行稳定性，同时机翼与尾翼距离存在改善飞行稳定性最优值。研究结果可为翼尖铰接组合式无人机设计提供指导和参考。

The wingtip-hinged multi-body combined Unmanned Aerial Vehicle （UAV） represents a novel conceptual aircraft， comprising multiple individual unmanned aircraft interconnected through wingtip hinges and allowing for relative roll motion. It exhibits significant distinctions in layout parameters and flight dynamics characteristics compared to conventional aircraft， with the presence of aerodynamic coupling between individual unmanned aircraft. First， the state-space vortex lattice method is employed to derive the aerodynamic derivatives specific to this aircraft type. Then， utilizing the Newton-Euler equations， a flight dynamics model is established for trim calculation and stability analysis， elucidating its unstable compound motion flight modes dominated by relative roll motion. Lastly， an investigation is conducted on the influence of layout parameters on flight dynamics stability. The analysis shows that reducing the trim roll angle of individual unmanned aircraft and increasing the sweep angle can enhance flight stability， while an optimal distance between the wing and tail is found to improve flight stability. The research findings can provide guidance and reference for the design of wingtip-hinged multi-body combined UAVs.