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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。
Compared with the conventional layout aircraft, the wing layout aircraft has the advantages of light weight, high flexural strength, low induced resistance, large lift coefficient and good stability. A highly efficient numerical simulation method is introduced to complete the preliminary calculation and analysis of the aerodynamic characteristics of a UAV with a type of wing layout. Based on the commercial software ANSYS, the whole research process focuses on three aspects of the modeling of the grid, the flow field simulation of the whole machine and the analysis of the aerodynamic simulation data to explore the aerodynamic characteristics of the longitudinal, lateral and heading of the UAV and the manipulation of the main control surface Efficiency, to achieve the UAV stability and maneuverability characterization and evaluation. The results show that the variation of the declination angle of the UAV does not affect the grip stability of the UAV. In the range of 0 ° ~ 25 ° declination, the lift coefficient and the lift coefficient of the elevator Linear variation; in the angle of attack of -4 ° ~ 12 °, with the increasing angle of attack, the horizontal static stability of the UAV is greater; two vertical wings and vertical tail is generated heading Static stability of the main components.