铰接式旋翼舰面瞬态气弹响应及参数研究

为了研究舰面铰接式旋翼桨叶桨尖与机体相碰的原因及参数影响,本文采用中等变形梁模型处理桨叶弹性变形,用有限转角模拟桨叶绕铰刚性运动和非线性准定常气动模型处理气动力。通过与国外计算及试验数据的相关性分析,验证了本文建模及计算方法的正确性。参数分析表明:1)挥舞限动块脱开前,桨叶弹性变形提供的桨尖挥舞位移占主要部分,脱开后,桨叶刚性运动提供的桨尖挥舞位移占主要部分;2)舰面流场采用梯形流时,计算的桨尖挥舞位移最大;3)挥舞限动角大小及离心式限动块释放时间对桨尖最大挥舞位移影响不明显;4)直接增加桨叶挥舞刚度可显著地减小桨尖向下最大挥舞位移;5)随总距增加,桨尖挥舞挠度减小不明显,这是通过增加总距来减小桨叶挥舞位移不可行的另一原因。

Analysis of transient aerolastic response for shipboard articulate rotor

To investigate the mechanism and parameter influence of the blade tip impact to fuselage for shipboard articulate helicopter,the moderate deflection beam model and the nonlinear quasi-steady aerodynamic model were adopted.Finite rotation was used to simulate the motions of hinges.Computation results of this paper are in good agreement with test data and other work's results.Parameter study shows: 1) before the releasing of flap stop,the elastic deflection provides the majority of flap displacement,while after releasing,the rigid motion provides the greater part;2) adopting step flow,computation of blade tip flap displacement is the largest of the three adopted math model of shipboard flow field;3) adjusting flap droop stop angle or the releasing time of flap droop stop has only a little effect on the negative maximum flap displacement;4) directly increasing the flap stiffness of blade can distinctly reduce the negative maximum flap displacement;5) with the increasing of collective pitch,the decrease of blade tip flap displacement is not distinct and this is another reason why the method of increasing collective pitch can't be adopted.