直升机旋翼与平尾间的非定常气动干扰在低速飞行时尤为突出，易诱发强非线性载荷，显著影响纵向稳定性与操纵品质。现有建模方法难以兼顾精度与效率，且多依赖国外闭源工具，限制了其在全包线飞行动力学与控制中的应用。本文提出一种高效降阶建模方法，融合自主开发的粘性涡粒子法（VPM）与系统辨识技术。基于高保真VPM尾迹数据，通过“VPM模拟–频响分析–系统辨识”一体化流程，构建以尾迹倾斜角为统一自变量、传递函数形式表征的旋翼/平尾干扰模型，并引入三维采样点合成与时延机制，显式刻画平尾所受非均匀动态干扰。验证表明：在飞行力学核心频段（<10 rad/s）内，模型与风洞试验最大误差为8.7%；旋翼单转计算耗时约0.224毫秒，较VPM提升逾四个数量级，满足实时仿真需求。该方法理论上具备良好泛化潜力与工程适用性，可为直升机高置信度数字飞行动力学建模与智能飞行控制提供高效、可靠的气动干扰建模支撑。
The unsteady aerodynamic interaction between the helicopter rotor and horizontal tail is particularly pronounced during low-speed flight, which can induce strongly nonlinear loads and significantly affect longitudinal stability and handling qualities. Existing ap-proaches struggle to balance accuracy with efficiency and often rely on closed-source foreign tools, limiting their application in full-envelope flight dynamics and control. This paper proposes an efficient reduced-order modeling method that integrates an inde-pendently developed Viscous Vortex Particle Method (VPM) with system identification techniques. Based on high-fidelity VPM wake data, a unified workflow—"VPM simulation–frequency response analysis–system identification"—is employed to construct a rotor/horizontal tail interaction model. This model uses wake skew angle as a unified independent variable and is expressed in trans-fer function form, incorporating three-dimensional sampling point synthesis and a time-delay mechanism to explicitly capture the non-uniform dynamic disturbances acting on the horizontal tail. Validation results show that within the core frequency range of flight dynamics (<10 rad/s), the maximum discrepancy between the model and wind tunnel tests is 8.7%. The computational cost for a single rotor revolution is approximately 0.224 milliseconds, representing an improvement of over four orders of magnitude com-pared to the full VPM simulation, thereby meeting real-time simulation requirements. The proposed method exhibits strong generali-zation capability in theory and engineering applicability, providing efficient and reliable aerodynamic interaction modeling support for high-fidelity digital flight dynamics modeling and intelligent flight control of helicopters.
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