论文部分内容阅读
动态失速的发生会在直升机旋翼桨叶和桨毂上产生高的交变扭转振动载荷,并限制直升机高速重载状态下的使用包线。本文利用计算流体力学(CFD)方法对基于充气前缘(ILE)技术的SC1095旋翼翼型动态失速抑制进行研究,分析了ILE抑制动态失速的控制机理,获得了ILE结构布置和充放气方式对动态失速的影响规律。研究表明:ILE可以有效抑制动态失速的发生;ILE最大膨胀程度越大,其抑制动态失速的效果越好,但膨胀程度过大后抑制效果开始减弱;ILE在翼型上仰至最大迎角时恰好达到最大膨胀状态,其对动态失速的抑制效果最好;ILE保持最大膨胀状态的时间长短对抑制效果影响不大;在翼型上仰至不同迎角时开始对ILE充气会对动态失速抑制有较大影响;ILE整流段与翼型连接位置对动态失速抑制有很大影响,整流段越长,抑制效果越好。
The occurrence of dynamic stalls creates high alternating torsional vibration loads on the helicopter rotor blades and hubs and limits the use of helidets for high-speed, heavy-load helicopters. In this paper, the CFD method is used to study the dynamic stall control of SC1095 rotor airfoil based on Inflatable Leading Edge (ILE) technology. The control mechanism of ILE suppressing dynamic stall is analyzed, and the ILE structural layout and the method of charging and discharging are obtained The influence law of dynamic stall. The results show that: ILE can effectively inhibit the occurrence of dynamic stall; the larger the ILE maximum expansion, the better the effect of inhibiting dynamic stall, but the suppression effect begins to decrease after the expansion degree is too large; Just to reach the maximum expansion state, which has the best effect on the dynamic stall inhibition; ILE maintain the maximum expansion state of the length of time has little effect on the suppression; starting on the airfoil up to different angle of attack ILE will be dynamic stall control Has a greater impact; ILE rectifier section and the airfoil connection position has a significant impact on the dynamic stall control, the longer the rectifier segment, the better the suppression effect.