This paper presents a stochastic approach for modeling the turbulent airwake suitable for real-time simulation of the helicopter–ship dynamic interface. This approach relies on the measurements of unsteady loads collected during a wind-tunnel test campaign with a scaled helicopter operating over the deck of simple frigate shape 1. Power spectral densities of the measured aerodynamic loads combined with the estimated frequency response functions are used to find, through an optimization algorithm, a model of airwake spectra over the range of frequencies which mainly affects the pilot workload during shipboard operations. Then, a set of autoregressive filters is designed for every particular rotor position and wind-over-deck condition, so that when driven by white noise, the spectrum of the output will reproduce those obtained from the optimization. This approach is applied to three different tested wind directions and three rotor positions by implementing the autoregressive filters into the multibody model of the experimental rotor. Frequency response analysis of the aerodynamic loads demonstrates that the turbulent airwake model obtained from the experimental data can predict the unsteadiness of loads comparable to those measured in the wind tunnel across the bandwidth of interest for pilot activities. The identified airwake models could be applied to a full-scale model to simulate the unsteady loads effectively experienced by the helicopter during a ship landing flight.

本文提出了一种适用于直升机-船舶动态界面实时模拟的湍流空气尾流建模的随机方法。该方法依赖于在风洞测试活动期间收集的不稳定载荷的测量，其中一架缩放直升机在简单护卫舰形状 1 的甲板上运行。测量的空气动力载荷的功率谱密度与估计的频率响应函数相结合，用于找到，通过优化算法，建立了频率范围内的尾流频谱模型，该模型主要影响舰载操作期间飞行员的工作量。然后，针对每个特定的转子位置和甲板风条件设计了一组自回归滤波器，以便在白噪声驱动时，输出频谱将再现从优化中获得的频谱。通过将自回归滤波器应用到实验转子的多体模型中，该方法适用于三个不同的测试风向和三个转子位置。空气动力载荷的频率响应分析表明，从实验数据获得的湍流尾流模型可以预测载荷的不稳定性，与在飞行员活动感兴趣的带宽上在风洞中测量的载荷相当。确定的空气尾流模型可以应用于全尺寸模型，以模拟直升机在船舶着陆飞行期间有效经历的非定常载荷。