共轴刚性旋翼振动载荷影响分析  

Structural Load Influence Analysis of Coaxial Rigid Rotor

作　　者：谭水鹏 王宇奇[1] 虞志浩[2] TAN Shuipeng;WANG Yuqi;YU Zhihao(China Helicopter Research and Development Institute,Jingdezhen 333001,China;National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《直升机技术》2024年第3期18-25,30,共9页Helicopter Technique

摘　　要：针对共轴刚性旋翼建立了气动弹性分析模型,开展旋翼载荷影响分析。气动弹性分析模型中采用几何精确桨叶结构动力学模型和旋翼自由尾迹模型,并结合松耦合方法计算共轴刚性旋翼载荷。通过XH-59A和X2悬停及前飞试验状态,验证了理论模型。分析了旋翼桨叶片数、交叠方位角、轴前倾角等结构参数和飞行状态参数对共轴刚性旋翼振动载荷的影响。结果表明:同等实度下旋翼桨叶片数增加,振动载荷降低;奇偶片桨叶交叠角相对机身的分布,显著影响横向和纵向振动载荷水平;相同升力和升力偏置(LOS)下轴前倾角增加,振动载荷增加。An aeroelastic analysis model was established for the coaxial rigid rotor,and the analysis of the influence of the rotor load was carried out.In the aeroelastic analysis model,the geometrically accurate blade structure dynamics model and the rotor free wake model were used,and the coaxial rigid rotor load was calculated in combination with the loose coupling method.The theoretical model was validated with the XH-59A and X2 hover and forward flight test states.The effects of structural parameters such as the number of rotor blades,overlapping azimuth angle,shaft forward inclination angle,and flight state parameters on the vibration load of the coaxial rigid rotor were analyzed.The results showed that the number of rotor blades increased and the vibration load decreased under the same solidity,the distribution of the odd-even blade overlap angle relative to the fuselage significantly affected the lateral and longitudinal vibration load levels,the shaft under the same lift and lift offset(LOS)as the rake angle increased,the vibration load increased.

关 键 词：直升机 振动 载荷 共轴刚性旋翼 气动弹性分析 

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] V214.33