基于黏性涡粒子尾迹模型的高速直升机配平特性分析  

Trim Characteristics Analysis on High-speed Helicopter Using Viscous Vortex Particles Wake Model

作　　者：徐川 刘长文[1] 鲁可[1] 汪正中[1] Xu Chuan;Liu Zhangwen;Lu Ke;Wang Zhengzhong(Science and Technology on Rotorcraft Aeromechanics Laboratory,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重点实验室,江西景德镇333001

出　　处：《航空科学技术》2023年第5期38-45,共8页Aeronautical Science & Technology

摘　　要：刚性旋翼高速直升机旋翼间复杂的尾迹干扰作用会影响其配平特性。针对这一问题,本文采用黏性涡粒子方法来精确计算上下旋翼复杂尾迹流场下的诱导速度,桨叶环量则采用涡面元法进行求解,两种方法耦合建立了尾迹模型。基于此尾迹模型进行高速直升机飞行动力学建模,包括结合刚性旋翼挥舞运动模型和变距操纵模型的旋翼尾迹气动力建模、机身以及平/垂尾气动力建模。同时与风洞试验结果对比,先验证了旋翼气动力模型的准确性,在此基础上,以XH-59A直升机为研究对象,计算得到了0~80m/s速度下的配平特性结果,与飞行试验数据对比良好,验证了飞行动力学模型的有效性。最后分析了悬停及低速前飞时旋翼间尾迹流场干扰对全机配平特性的影响。The flight dynamics characteristics of the rigid rotor high-speed helicopter are affected by the complex wake interference of the rotor.To overcome this problem,this paper utilizes the viscous vortex particles method to calculate the induced velocity of the coaxial rotor interference flow field and builds corresponding wake model.The circulation of the blade attached vortex and new vortex are calculated by using vortex panel method.In this paper,the aerodynamic model of the coaxial rotor is built by the viscous vortex particle wake model,the equivalent flapping motion and the pitch control motion.The accuracy of the model is assessed by a comparison with wind tunnel experimental data.Based on this,the flight dynamics model of the rigid rotor high-speed helicopter flight is built with fuselage model and horizontal/vertical tail model.Trim characteristics of XH-59A helicopter are analyzed,and flight dynamics model is verified by the flight test data.Finally,the influence of aerodynamic interference between upper and lower rotor in trim characteristics during hover and low-speed forward flight is analyzed.

关 键 词：直升机 黏性涡粒子 旋翼尾迹 飞行动力学 配平特性 

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]