共轴高速直升机飞行力学建模与验证  

Flight dynamic modeling and verification of coaxial high-speed helicopter

作　　者：陈立霞[1] 辛冀[1] CHEN Lixia;XIN Ji(National Key Laboratory of Rotorcraft Aeromechanics,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所直升机旋翼动力学国家级重点实验室,江西景德镇333001

出　　处：《飞行力学》2022年第2期25-32,共8页Flight Dynamics

摘　　要：针对共轴双旋翼带尾推力桨构型的高速直升机的多旋翼气动干扰问题,发展了一种不同转速多旋翼的时间步进自由尾迹模型。将多旋翼复杂气动干扰的诱导速度分析结果整理成表,为飞行力学计算中的旋翼非均匀入流模型提供修正数据,从而降低计算量、提高分析精度。对共轴高速直升机的刚性桨叶进行挥舞模态一阶等效,建立了兼顾精度和计算效率的共轴高速直升机飞行动力学模型,并将旋翼试验结果与XH-59A的试飞数据进行了对比验证。结果表明:所建模型对旋翼气动力计算误差小于10%;而在飞行力学分析中,相比于自由尾迹方法大幅降低了计算量,且总距、横向周期变距和总距差动等通道计算误差均小于1°。In accordance to the multi-aerodynamic surfaces of a high-speed helicopter with a configuration of coaxial rotors with propeller, a time stepping free wake model of multi rotor at different speeds is developed. The induced velocity analysis results of multi rotor complex aerodynamic interference are sorted into a table to provide correction data for the rotor non-uniform inflow model in flight mechanics calculation, so as to reduce the amount of calculation and improve the analysis accuracy. Based on the first-order equivalent flutter mode of the rigid blade of the coaxial high-speed helicopter, a flight dynamics model of the coaxial high-speed helicopter considering accuracy and computational efficiency is established, and the rotor test results are verified with the flight test data of XH-59A. The results show that the calculation error of rotor aerodynamic force by the model is less than 10%. In flight mechanics analysis, compared with the free wake method, the calculation amount is greatly reduced, and the calculation errors of collective pitch, lateral cyclic pitch and collective differential are less than 1°.

关 键 词：直升机 飞行力学 共轴刚性旋翼 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]