导　　师： 夏品奇

学科专业： 082501

授予学位： 硕士

作　　者： ;

机构地区： 南京航空航天大学

摘　　要： 重型直升机旋翼气动性能是发展重型直升机的一项关键技术,研究意义重大。 重型直升机旋翼桨叶片数较多,桨//涡干扰随之增加。基于升力面//涡格法建立的桨叶气动模型能够较充分地反映附着涡面各元素及其与尾迹之间的相互作用,因此,升力面理论可以改进桨//涡干扰增加情况下大变化诱导速度和载荷的计算精度。 本文建立了基于升力面//涡格法的重型直升机悬停和前飞预定尾迹模型。悬停状态时,悬停尾迹模型采用回流计算法来增加旋翼入流,通过算例与重型直升机实验数据对比,验证了模型的可靠性,然后将悬停尾迹模型用于计算桨叶展弦比、桨叶片数、线性扭转和分段线性扭转对悬停性能的影响,重点是分段线性扭转的影响;前飞状态时,应用前飞尾迹模型计算前飞桨叶载荷、前飞功率和旋翼升阻比,将计算结果先与中型直升机的实验数据相比较,验证了前飞尾迹模型的可靠性,然后计算重型直升机前飞性能,再将前飞尾迹模型用于计算桨叶桨尖形状、线性扭转和分段线性扭转对前飞性能的影响,重点是分段线性扭转的影响。计算得到了重型直升机悬停和前飞的气动特点及桨叶参数的影响特点。 The aerodynamic performance of heavy-lift helicopter rotor is a critical technology in development of the heavy-lift helicopter technology. Its research is significant. Many blades are used in heavy-lift helicopter, leading to largely increased interactions between blades and vortex. The bound vortex wake of the elements and their interactions with rotor wake can be reflected more adequately in the blade aerodynamic model based on the lifting surface // vortex lattice method. Therefore, the lifting surface theory can improve the calculation accuracy of greatly changed induced velocity and airloads when the condition of increasing blade//vortex interactions. In this thesis, the prescribed wake model of heavy-lift helicopter in hover and forward flight has been developed based on lifting surface // vortex lattice method. In hover, the inflow is added to the hover wake model by using the recirculation mechanism, the comparisons between the case studies and experimental data verified the developed model. The hover wake model of the heavy-lift helicopter was used to calculate the effects of number of blades, aspect ratio, linear blade twist and double linear blade twist on the hover aerodynamic performance of rotor, emphasizing the effects of double linear blade twist. In forward flight, blade airloads, flight power and rotor lift-to-drag ratio were calculated using the forward flight model. The comparisons between the numerical results and the experimental data of medium helicopters verified the developed model, then the heavy-lift helicopter forward flight performance was calculated. The forward flight wake model was used to calculate the effects of blade tip, linear blade twist and double linear blade twist on the forward aerodynamic performance, emphasizing the effects of double linear blade twist. The characteristics of heavy-lift helicopter hover performance, forward flight performance and the effects of blade parameters on heavy-lift helicopter performance were obtained.

关 键 词： 重型直升机 旋翼气动性能 升力面 涡格法 尾迹 桨叶参数 分段线性扭转

领　　域： [航空宇航科学与技术]