直升机旋翼瞬态气动响应分析的一个高效方法

Efficient Method for Helicopter Rotor Transient Aerodynamic Response

基于旋翼动量-叶素组合理论,计入桨叶挥舞运动和动态入流对旋翼拉力的非定常影响,建立了一个快速计算垂直飞行状态总距突增时旋翼气动响应的方法,可用于旋翼拉力、桨叶挥舞运动和诱导速度的瞬态变化的分析。为验证方法的有效性,分别对三种不同总距突增情况下的旋翼气动响应进行了计算,并与可得到的实验结果进行了对比。应用该方法,研究了铰接式旋翼桨叶的挥舞铰外伸量对动态响应的影响,对比了总距突增和突减两种情况下的不同瞬态变化。在此基础上,得出了一些结论。

An efficient method is presented to evaluate the rotor transient response to a ramp increase in collective pitch in vertical flight,where the unsteady effects of the blade flap motion and dynamic inflow on rotor thrust are taken into account based on the blade element/momentum theory,which is suitable for analyses of transient variation of rotor thrust,blade flap motion and induced velocity.To validate the proposed method,the calculations for rotor aerodynamic responses following a step increase in collective for three situations are carried out and compared with the available experimental data.The effects of the offset of blade flap hinge on the dynamic response are examined,and the different transient responses to the step increase and decrease in collective for an articulated rotor are analyzed comparatively.