基于自由尾迹和升力面方法的四旋翼气动干扰分析  

Analysis of quadrotor aerodynamic interference based on free wake and lift surface method

作　　者：赵其凯 陈仁良 ZHAO Qikai;CHEN Renliang(National Key Laboratory of Rotorcraft Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]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：《飞行力学》2022年第2期33-38,共6页Flight Dynamics

基　　金：江苏高校优势学科建设工程资助项目。

摘　　要：为研究悬停与小速度前飞状态下四旋翼直升机四副旋翼之间的气动干扰,建立了一种适用于多个旋翼气动干扰分析的计算方法。该方法桨叶模型采用升力面/涡格法,尾迹使用畸变的自由尾迹模型。然后,计算单旋翼与纵列式旋翼的气动性能,并与试验值对比,以验证方法的有效性。最后,将配平的四副旋翼置入同一流场,来自其他旋翼的干扰会改变四副旋翼的力和力矩,计算了这些力和力矩的变化并对计算结果进行了分析。结果表明:在悬停和小速度前飞时,由于干扰,四旋翼前方的两副旋翼拉力增加、功率减小,后方的两副旋翼在距离前方旋翼尾迹较近时拉力减小,功率增加。In order to study the aerodynamic interference between the four rotors of a quadrotor helicopter in hovering and low speed forward flight, a method has been established to calculate the aerodynamic interference between rotors. In this method, the lift surface method was used for blade model and distorted free wake model. Then, it was verified by calculating the aerodynamic performance of single and longitudinal rotor and comparing with the experimental results. Finally, four balanced rotors were placed in the same field, the interference from other rotors changed the force and moment of the four rotors and these changes were calculated and analyzed. The results show that during hover and low speed forward fight, the two forward rotors of quadrotor increase the lift force and decrease the power due to interference, while the two rear rotors of quadrotor decrease the lift force and increase the power when close to the forward rotors wake.

关 键 词：直升机 四旋翼 自由尾迹 气动干扰 

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]