地貌条件对扑翼飞行器气动特性的影响分析
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摘要
为更加真实可靠地反映扑翼飞行器在大气边界层中的飞行状态,采用基于标准的k-ε湍流模型,以大气边界层中四种具体地貌的风速剖面为入口边界条件,结合Fluent的滑移网格技术,分别对扑翼飞行器位置高度在标准高度以上和以下位置的气动特性进行数值模拟,分别得到两个位置的升阻力系数。计算结果表明,在翅翼扑动频率、入口风速剖面和迎角不变的情况下,地面粗糙度对扑翼飞行器升阻力系数的影响由扑翼飞行器相对于标准参考高度的位置决定。
In order to reflect the flying state of flapping-wing aircraft in atmospheric boundary layer more reliably, and using the standard k-ε turbulence model, in this paper, the aerodynamic characteristics of the flapping-wing vehicle position height above and below the normal height are numerically simulated with the wind velocity profile of four specific geomorphological in the atmospheric boundary layer as the inlet boundary condition, and the sliding mesh technology of fluent is combined. The aerodynamic characteristics of flapping-wing vehicle position height above and below the normal height are numerically simulated, and the lift and drag coefficients of two positions are obtained respectively. The results show that the effect of the ground roughness to the lift and drag coefficients of flapping-wing vehicle is decided by the position of flapping-wing aircraft relative to the normal height in the case of the wing flapping frequency, the inlet wind profile and the angle of attack.
In order to reflect the flying state of flapping-wing aircraft in atmospheric boundary layer more reliably, and using the standard k-ε turbulence model, in this paper, the aerodynamic characteristics of the flapping-wing vehicle position height above and below the normal height are numerically simulated with the wind velocity profile of four specific geomorphological in the atmospheric boundary layer as the inlet boundary condition, and the sliding mesh technology of fluent is combined. The aerodynamic characteristics of flapping-wing vehicle position height above and below the normal height are numerically simulated, and the lift and drag coefficients of two positions are obtained respectively. The results show that the effect of the ground roughness to the lift and drag coefficients of flapping-wing vehicle is decided by the position of flapping-wing aircraft relative to the normal height in the case of the wing flapping frequency, the inlet wind profile and the angle of attack.
引文
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[2]John G,Alex H,Ariel P R,et al.Robo raven:a flappingwing air vehicle with highly compliant and independently controlled wings[J].Soft Robotics,2014,1(4):275-288.
[3]Mostafa H,Abdessattar A,Wei Mingjun,et al.A novel methodology for wing sizing of bio-inspired flapping wing micro air vehicles:theory and prototype[J].Acta Mechanica,2017,228(3):1097-1113.
[4]He Wei,Yan Zichen,Sun Changyin,et al.Adaptive neural network control of a flapping wing micro aerial vehicle with disturbance observer[J].IEEE Transactions on Cybernetics,2017,47(10):3452-3465.
[5]杜强,杜平安.大气边界层中天线风载特性的数值分析[J].电子科技大学学报,2010,39(02):169-172.