基于涡管模型的倾转四旋翼气动干扰快速分析  

Fast analysis of aerodynamic interference for quad-tiltrotor based on vortex tube model

作　　者：王冶平 吉洪蕾 周攀 叶毅 WANG Yeping;JI Honglei;ZHOU Pan;YE Yi(College of Aerospace Engineering,Chongqing University,Chongqing 400044,China;Key Laboratory of Rotor Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]重庆大学航空航天学院,重庆400044 [2]中国空气动力研究与发展中心旋翼空气动力学重点实验室,绵阳621000 [3]南京航空航天大学航空学院,南京210016

出　　处：《航空学报》2025年第2期206-221,共16页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11902052);重庆市自然科学基金(CSTB2022NSCQ-MSX1592);中国空气动力研究与发展中心旋翼空气动力学重点实验室研究开放课题(RAL202302-3)。

摘　　要：针对倾转四旋翼飞行器总体设计和飞行动力学建模时难以准确快速评估旋翼间气动干扰的问题,发展基于涡管尾迹模型的多旋翼气动干扰快速分析方法。基于经典涡流理论假设,将各副旋翼尾迹涡系抽象为一根半无限长的涡管,推导旋翼涡管尾迹对空间任意一点诱导速度的半解析解,形成多旋翼间气动干扰的高效计算方法,并与旋翼自诱导速度的动态入流模型结合,建立准确高效的多旋翼诱导速度计算模型。在此基础上,采用共轴和纵列式双旋翼拉力-功率性能曲线的风洞试验结果验证模型。最后,针对某倾转四旋翼飞行器缩比模型分析其直升机模式和倾转过渡时四副旋翼之间的气动干扰特性。结果表明:该模型能够较为准确地捕捉旋翼垂直和水平间距对旋翼间气动干扰的影响,可以用于多旋翼气动干扰快速分析;倾转四旋翼飞行器在直升机模式附近的旋翼间气动干扰特性变化剧烈,合理的气动布局和旋翼旋转方向设计能够有效改善受干扰旋翼桨盘平面的诱导速度及载荷分布。ed as a semi-infinite vortex tube,and a semi-analytical solution for the induced velocity at any point in space by rotor vortex tubes is derived.This forms an efficient computation method for aerodynamic interference between multirotor.Combined with the dynamic inflow model accounting for rotor self-induced velocity,an accurate and efficient model for calculating the induced velocity in multirotor is established.Based on this,the model is validated using wind tunnel test results of thrust-power performance curves for coaxial and tandem rotors.Finally,the aerodynamic interference characteristics between the four rotors of a scaled model of a quad-tiltrotor aircraft are analyzed during the helicopter mode and tilt transition mode.The results show that the model can capture the influence of vertical and horizontal spacing on aerodynamic interference between rotors relatively and accurately,making it suitable for fast analysis of multirotor aerodynamic interference.The aerodynamic interference characteristics between rotors near the helicopter mode of quad-tiltrotor aircraft vary significantly.A reasonable aerodynamic layout and rotor rotation direction design can effectively improve the induced velocity of the disturbed rotor and the load distribution on the rotor disc.

关 键 词：倾转四旋翼 涡管尾迹 气动干扰 诱导速度 飞行动力学 

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]