某型联翼布局无人机的气动计算与分析

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。

Aerodynamic calculation and analysis of a canard joined-wing UAV

Joined-wing configuration has lower structural weight, higher torsional/flexural strength, smaller induced drag, bigger lift coefficient, and better stability than the normal one. The purpose of this paper is to provide an effective numerical simulation method for calculation and analysis of aerodynamic characteristics of a canard joined-wing UAV. The whole research process of the UAV based on commercial software ANSYS consists of grid modeling, simulations of the flow field of the UAV, qualitative and quantitative analyses of the aerodynamic data. By means of exploring the longitudinal, lateral and directional stability of the UAV, control devices efficiency, we can finally achieve the evaluation of the UAV flight performance. According to preliminary evaluation of the UAV flight performance, we can well complete the design modifications before trial production of the UAV. In addition, the preliminary design optimization of the UAV based on the numerical simulation results will greatly shorten the overall design time, and reduce research costs of the UAV. This present work is helpful for the future aerodynamic analysis of joined-wing UAVs.