摘要
对不同变距轴线方案下的共轴刚性旋翼桨叶气动铰链力矩特性进行了计算分析。以X2共轴刚性旋翼气动布局为研究对象,气动铰链力矩计算方法采用自由尾迹方法。变距轴线方案包括常规变距方案以及X2共轴刚性旋翼采用的新型变距轴线方案。常规方案下变距轴线设置在桨叶剖面0.25弦点,新方案下变距轴线在桨叶根部剖面设置在0.5弦点,在特定的径向剖面过渡至0.25弦点。对比了不同方案下旋翼气动铰链力矩的静态平均值和动态1/2峰-峰值。对X2旋翼气动布局进行桨尖后掠处理,分析了桨尖后掠构型下的气动铰链力矩特点。结果表明,新型变距轴线方案下铰链力矩的静态值和动态值均有很大程度的减小,降低幅度随着前飞速度的增加而增大。
The blade aerodynamic hinge moment of coaxial rigid rotor with different blade pith axis concepts was analyzed.Free wake method was used during the analysis,and the X2 rotor aerodynamic configuration was chosen as research object.The blade pith axis concepts include conventional concept and new concepts which were used by recent X2 coaxial rigid rotor configurations.The blade pith axis was set on quarter chord in the conventional concept,while in the new concept pith axis was set on half chord at blade root and then translated to quarter chord at specific radial location.The static mean value and the half peak-peak value of the blade aerodynamic hinge moment results were compared.Then,the X2 rotor blade tip was modified,the blade aerodynamic hinge moment of rotor configuration with back sweep blade tip was investigated.The results show that,the new blade pith axis concept reduce both the mean value and the the half peak-peak value of hinge moment,and the reduction increases as the flight speed increase.
作者
袁明川
孙朋朋
樊枫
刘平安
林永峰
Yuan Mingchuan;Sun Pengpeng;Fan Feng;Liu Pingan;Lin Yongfeng(Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen 333001, China)
出处
《航空科学技术》
2018年第4期61-66,共6页
Aeronautical Science & Technology
关键词
共轴刚性旋翼
铰链力矩
自由尾迹
变距轴线
后掠桨尖
coaxial rigid rotor
hinge moment
free wake
blade pith axis
back sweep blade tip
