The effectiveness of active flow control for reducing vibrations in helicopter rotors is examined using numerical simulations. The flow control actuators employ pulsed fluidic jets on the pressure side (PS) and suction side (SS) of the airfoil and are installed near the trailing edge of the blades. The flow control region extends over 12% of the blade span and is centered at the 75% span location. A reduced-order model (ROM) of the unsteady aerodynamic effects introduced by the actuators is developed. The ROM is trained using data obtained from unsteady Reynolds-averaged Navier–Stokes simulations performed across a broad range of flow conditions representing the rotor environment. The ROM is incorporated in a comprehensive aeroelastic rotor simulation code. Open-loop control, consisting of alternating PS and SS actuation at various frequencies, is applied on a four-blade hingeless rotor resembling the Messerschmitt–Bölkow–Blohm Bo-105 rotor in level flight with an advance ratio of 0.30. The results indicate that the flow control actuators have significant control authority to modify the vibratory loads, with up to 85% reduction in the four-per-revolution vertical shear force at the rotor hub. The tradeoff between vibratory load reduction and rotor performance is also examined. A 5.3% increase in rotor power accompanies the vibratory load reduction.

使用数值模拟检验了主动流动控制对减少直升机旋翼振动的有效性。流量控制执行器在翼型的压力侧 (PS) 和吸力侧 (SS) 上采用脉冲射流，并安装在叶片后缘附近。流量控制区域延伸超过叶片跨度的 12%，并以 75% 跨度位置为中心。开发了致动器引入的非定常空气动力学效应的降阶模型 (ROM)。ROM 使用从非定常雷诺平均 Navier-Stokes 模拟中获得的数据进行训练，该模拟在代表转子环境的各种流动条件下进行。ROM 包含在综合的气动弹性转子模拟代码中。开环控制，由不同频率下的交替 PS 和 SS 驱动组成，应用在类似于 Messerschmitt-Bölkow-Blohm Bo-105 转子的四叶片无铰链转子上，推进比为 0.30。结果表明，流量控制执行器具有显着的控制权来修改振动载荷，转子轮毂每转四次的垂直剪切力降低了 85%。还检查了振动负载降低和转子性能之间的权衡。伴随着振动载荷的减少，转子功率增加了 5.3%。转子轮毂处每转四次的垂直剪切力降低多达 85%。还检查了振动负载降低和转子性能之间的权衡。伴随着振动载荷的减少，转子功率增加了 5.3%。转子轮毂处每转四次的垂直剪切力降低多达 85%。还检查了振动负载降低和转子性能之间的权衡。伴随着振动载荷的减少，转子功率增加了 5.3%。