某型联翼布局无人机的气动计算与分析

Aerodynamic Calculation and Analysis of a Joined-wing Unmanned Aerial Vehicle

与常规布局飞机相比,联翼布局飞机具有结构重量轻、抗弯扭强度大、诱导阻力低、升力系数大和稳定性好等优点。介绍一种高效的数值模拟方法,完成对某型联翼布局无人机气动特性的初步计算与分析。基于商业软件ANSYS,整个研究过程着重于从网格建模、全机流场模拟、气动模拟数据分析三个方面,探索该型无人机纵向、横向和航向的气动特性以及主操纵面的操纵效率,实现对该型无人机稳定性和操纵性能的表征与评估。结果表明:无人机升降舵偏角的变化不影响无人机的握杆静稳定度,并且在0°~25°的升降舵偏角(下偏)范围内,升降舵偏角与升降舵的升力系数基本呈线性变化;在-4°~12°的迎角范围内,随着迎角的不断增大,该型无人机的横向静稳定性水平越大;两个垂直翼和垂尾是产生航向静稳定性的主要部件。

Joined-wing configuration has lower structural weight,higher torsional/flexural strength,smaller induced drag,bigger lift coefficient,and better stability than the normal one.An effective numerical simulation method for calculation and analysis of aerodynamic characteristics of a joined-wing unmanned aerial vehicle（UAV）is provided.The whole research process of the UAV based on commercial software ANSYS consists of grid modeling,simulations of the flow field of the UAV,analyses of the aerodynamic data.By means of exploring the longitudinal,lateral and directional stability of the UAV,control devices efficiency,the evaluation of the UAV flight performance are achieved.The results indicate that the variation of elevator deflection does not affect the stick-fixed static stability level of the UAV,and the lift coefficient of the elevator of the UAV increases linearly with downward elevator deflection angle in the range 0°～25°.The level of the lateral static stability of the UAV increases as the angle of attack increases in the range-4°～12°.The contribution of the directional stability of the UAV is dominated mainly by the two vertical wings and the vertical tail.