针对倾转旋翼机悬停、前飞和过渡模式旋翼/机翼的气动干扰特性，根据Neumann边界条件和Hess等效原则提出了一种快速分析旋翼/机翼气动干扰的改进混合涡粒子方法。通过引入单面元-多涡粒子转换和涡粒子自适应数量控制策略，实现了自适应涡粒子数量，进一步优化了计算效率。与旋翼风洞试验数据进行了对比，表明自适应数量混合涡粒子方法相较于传统黏性涡粒子方法可以在提高计算效率的同时得到与试验数据吻合良好的计算结果。随后开展旋翼/机翼气动干扰模型在悬停和过渡模式下的流场分析和数值模拟，探讨了旋翼/机翼气动干扰的影响。结果表明：旋翼/机翼气动干扰模型悬停时机翼阻塞下洗流，虽对旋翼有轻微的增升作用但机翼承受了更大的向下载荷，严重影响了旋翼/机翼模型的有效载荷；随着总距增加，机翼向下载荷引起的升力损失逐渐减小。直升机模式向飞机模式转换过程中，旋翼尾迹使机翼升力在倾转初期有明显损失，中期有明显提升，末期几乎无影响；机翼会改变旋翼的部分尾迹结构，但对旋翼性能影响较小。飞机模式前飞时，旋翼/机翼气动干扰较弱，但仍可观测到机翼的升阻比有所下降。这些发现将为倾转旋翼机气动弹性稳定性分析、高保真度飞行力学模型建立和性能优化提供有利支撑。

Aiming to elucidate the complex aerodynamic interactions between rotor and wing during hovering， forward flight， and transition modes of tiltrotor aircraft， an enhanced hybrid vortex particle method is developed. This method leverages Neumann boundary conditions and Hess equivalence principle for efficient computational analysis. By incorporating a single panel-multi vortex particles conversion and adaptive vortex particle quantity control， the adaptive adjustment of vortex particle quantity is achieved， further optimizing the computational efficiency.Validation against wind tunnel data demonstrates precision and efficiency of the method compared to traditional viscoelastic vortex particle methods. Subsequent numerical simulations and flow field analysis of the rotor/wing model unveil intricate aerodynamic interactions. In hovering mode， while the wing’s blocked downwash slightly enhances rotor lift， the dominant negative lift due to significant wing download adversely impacts overall load-carrying capacity. Increasing collective pitch mitigates this lift loss. During transition， the rotor wake initially induces substantial lift loss on the wing， followed by a notable increase and negligible influence in later phases. The wings alter structure of the rotor wake， but the effect on rotor performance is minimal. In forward flight， rotor/wing aerodynamic interactions is weak， albeit with a reduced lift-to-drag ratio. These findings provide valuable insights into the aerodynamic complexities of tiltrotor aircraft， contributing to the development of aeroelastic stability analysis， high-fidelity flight dynamics model development and performance optimization.