含不同桨尖的无轴承旋翼直升机气动机械稳定性  

Aeromechanical stability of bearingless rotor helicopter with different blade tip shapes

作　　者：张俊豪 夏品奇[1] ZHANG Jun-hao;XIA Pin-qi(National Key Laboratory of Rotorcraft Aeromechanics,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing210016,China)

机构地区：[1]南京航空航天大学航空宇航学院直升机旋翼动力学国家级重点实验室

出　　处：《振动工程学报》2019年第4期609-618,共10页Journal of Vibration Engineering

基　　金：国家自然科学基金资助项目(11572150);中国博士后科学基金资助项目(2018M642252)

摘　　要：直升机旋翼桨尖形状可以有效提高旋翼气动性能,但可能会降低旋翼气弹稳定性.这方面的研究包括不同桨尖形状的旋翼气动性能、孤立旋翼气弹稳定性、无铰式旋翼直升机气动机械稳定性.不同桨尖形状的无轴承旋翼直升机的气动机械稳定性研究还未见到报道.研究了含不同桨尖无轴承旋翼直升机的气动机械稳定性,基于哈密顿原理和中等变形梁理论,并通过桨尖形状引起的非线性位移协调条件,建立了含不同桨尖形状的无轴承旋翼/机体耦合系统的气动机械动力学模型.计算的ITR无轴承旋翼直升机地面共振和空中共振的稳定性与实验结果一致,证明了建立的气动机械动力学模型的准确性。计算了桨尖前掠、后掠、上反、下反、尖削和形状组合对无轴承旋翼直升机地面共振和空中共振稳定性的影响,计算结果表明,桨尖形状能有效改变无轴承旋翼直升机的气动机械稳定性.The blade tip shapes of helicopter rotor can improve the aerodynamic performance of rotor effectively, but may re-duce the aeroelastic stability of rotor. The studies in this area include the aerodynamic performance of rotor, the aeroelastic sta-bility of isolated rotor, and the aeromechanical stability of hingeless rotor with different blade tip shapes. The aeromechanical stability of bearingless rotor helicopter with different blade tip shapes has not been reported, and has been systemically investi-gated in this paper. Based on the Hamilton's principle and the moderate deflection beam theory, and through the nonlinear dis-placement compatibility conditions caused by the blade tip shapes, the aeromechanical dynamic model of bearingless rotor/fuselage coupled system with various blade tip shapes has been established.The calculated stability of ground resonance and air res-onance of the ITR bearingless rotor helicopter are consistent with the experimental results,verifying the aeromechanical dy-namic model established in this paper. The effects of blade tip sweep-forward,sweep-backward,anhedral, droop, taper and tip combination on the ground resonance and air resonance of bearingless rotor helicopter are calculated. The results indicate that the blade tip shapes can effectively change the aeromechanical stability of bearingless rotor helicopter.

关 键 词：旋翼/机体耦合系统 无轴承旋翼 桨尖形状 地面共振 空中共振 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程] V214.34