水平来流作用下无人机旋翼多维气动特征研究

doi:10.12382/bgxb.2024.0316

摘要/Abstract

摘要：

为研究水平来流对小型无人机旋翼气动特征的影响规律,采用风洞试验和仿真模拟的方法,获取不同来流速度下无人机旋翼轴向和旋转平面内的多维气动数据以及尾涡扩散特征。通过低速风洞模拟水平来流,采用六分量力-力矩传感器测量0~15m/s来流速度和2000~9000r/min转速范围内旋翼的z轴轴向和x-y旋转平面的气动力和力矩数据;试验研究着重分析了旋转平面内侧向力和俯仰滚转力矩的变化规律;仿真模拟结果讨论了来流速度对旋转周期内表面压力分布的影响和近场尾涡的形态特征。研究结果表明:水平来流作用下旋翼效率最优转速区间为4000~6000r/min;旋转平面内x轴力是主导侧向力,x轴和y轴力矩同时起作用,来流速度高于5m/s时侧向力和力矩不可忽视,动力学分析必须予以考虑;水平来流导致旋翼尾涡的对称特征破坏,来流速度越大、倾斜角越大,尾涡扩散发展受到挤压。

关键词: 无人机, 水平来流, 气动力, 旋翼尾涡, 侧向力, 俯仰滚转力矩

Abstract:

In order to study the effect of horizontal inflow on the aerodynamic characteristics of small unmanned aerial vehicle (UAV) rotors,the wind tunnel test and numerical simulation are conducted to obtain the multi-dimensional aerodynamic data and wake vortex diffusion characteristics of UAV rotors under different inflow speeds.A low-speed wind tunnel is used to simulate horizontal inflow,and a six-component force-moment sensor is used to measure the aerodynamic forces the rotational speeds from 2000r/min to 9000r/min.The experimental study focuses on analyzing the variations of lateral force,and pitch and roll moments in the rotational plane.The influence of inflow speed on surface pressure distribution during the rotational period and the morphological characteristics of the near-field wake vortex are discussed from the numerically simulated results.The results indicate that the optimal rotational speed range of rotor is 4000-6000r/min under the action of horizontal inflow The x-axis force in the rotational plane is the primary contributor to the lateral force,with both x-axis and y-axis moments playing roles simultaneously.The lateral forces and moments become significant at inflow speeds above 5m/s and must be considered in dynamic analysis.The horizontal inflow disrupts the symmetrical feature of the rotor wake vortex.The inflow with greater speed leads to a larger inclination angle,causing the diffusion evolution of wake vortex to be compressed.

Key words: unmanned aerial vehicle, horizontal inflow, aerodynamics, rotor wake vortex, lateral force, pitch and rolling moment

刘聪, 李百庆, 张宗卫, 单泽众. 水平来流作用下无人机旋翼多维气动特征研究[J]. 兵工学报, 2025, 46(3): 240316-.

LIU Cong, LI Baiqing, ZHANG Zongwei, SHAN Zezhong. Investigation of Multi-dimensional Aerodynamic Characteristics of UAV Rotor Subjected to Horizontal Inflow[J]. Acta Armamentarii, 2025, 46(3): 240316-.

图/表 19

图1 大尺寸低速风洞

Fig.1 Large-scaled low-speed wind tunnel

图2 旋翼六分量力/力矩试验台

Fig.2 Rotor’s six component force-torque experimental bench

图3 旋翼几何模型

Fig.3 Rotor geometric model

图4 旋翼弦长和扭转角分布

Fig.4 Chord length and twist angle distribution

图5 计算域及边界条件

Fig.5 Computational domain and boundary conditions

图6 计算网格

Fig.6 Computational mesh

图7 试验和CFD仿真的轴向拉力-扭矩结果随旋翼转速的变化

Fig.7 Variation of axial force-torques from experiment and CFD simulation with rotor speed

图8 不同来流速度下轴向拉力随旋翼转速的变化

Fig.8 Variation of axial force with rotor speed at different inflow velocities

图9 不同来流速度下轴向扭矩随旋翼转速的变化

Fig.9 Variation of axial torque with rotor speed at different inflow velocities

图10 不同来流速度下轴向拉力系数随旋翼转速的变化

Fig.10 Variation of axial force coefficient with rotor speed at different inflow velocities

图11 不同来流速度下轴向扭矩系数随旋翼转速的变化

Fig.11 Variation of axial torque coefficient with rotor speed at different inflow velocities

图12 不同来流速度下FM随旋翼转速的变化

Fig.12 Variation of figure of merit with rotor speed at different inflow velocities

图13 不同来流速度下侧向力随旋翼转速的变化

Fig.13 Variation of lateral force with rotor speed at different inflow velocities

图14 不同来流速度下侧向力系随旋翼转速的变化

Fig.14 Variation of lateral force coefficient with rotor speed at different inflow velocities

图15 不同来流速度下x轴力矩随旋翼转速的变化

Fig.15 Variation of x-axis moment with rotor speed at different inflow velocities

图16 不同来流速度下y轴力矩随旋翼转速的变化

Fig.16 Variation of y-axis momentwith rotor speed at different inflow velocities

图17 不同来流速度下旋翼表面压力分布

Fig.17 Surface pressure distribution at different inflow velocities

图18 不同来流速度下x轴力矩系数随旋翼转速的变化

Fig.18 Variation of x-axis moment coefficient with rotor speed at different inflow velocities

表1 来流速度对旋翼近场尾涡扩散分布影响

Table 1 Effect of inflow velocity on diffusion distribution of wake vortex in near field

转速/ (r·min^-1)	来流速度/(m·s^-1)
转速/ (r·min^-1)	0	5	10	15
2000
5000
8000

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