后翼参数对联接翼布局飞行性能影响研究

Impacts of Rear Wing Parameters on the Flight Performance of Joined-Wing UAV

与常规布局相比,联翼布局具有结构重量轻、抗弯扭强度大、诱导阻力低、升力系数大和稳定性好等优点。本文对一种联接翼布局无人机的几何气动外形进行了初步设计,并通过一个变量参数改变后翼几何外形,构造了此联接翼飞机的变形构型。采用CFD数值模拟方法,使用STARCCM+软件对飞机的外流场几何模型进行网格划分和仿真计算,得到并分析了联接翼布局的基本气动参数,包括升力系数、阻力系数、升阻特性、俯仰力矩系数等,对各参数下飞机的气动性能进行了计算和对比分析。结论表明,改变后翼外形参数对无人机升阻特性的影响较小,对俯仰特性的影响较大,适当修改后翼几何形状对改善联接翼布局的俯仰操纵能力有较好的帮助。为将联接翼布局飞机设计及相关理论研究提供一定的借鉴和参考。

Compared with conventional aerodynamic configuration, the joined-wing is characterized by light structural weight, high flexural and torsional strength, smaller induced drag, large lift coefficient and stability. In this paper, the geometric and aerodynamic shape of a joined-wing layout UAV is preliminarily designed, and the geometric shape of the rear wing is changed by a variable parame-ter to construct the deformation configuration of the joined-wing UAV. The geometric model of the aircraft’s outflow field was meshed and simulated by STARCCM+ software. The basic aerodynamic parameters of the joint wing layout scheme including lift coefficient, drag coefficient, lift-drag charac-teristic, pitching moment coefficient were obtained and analyzed. The results show that changing the profile parameters of the rear wing has less influence on the lift-drag characteristics and more influence on the pitching moment characteristics of the UAV, and proper modification of the geometry of the rear wing is helpful to improve the pitch control ability of the connected wing layout. It can be a reference in design and study of the joined wing aircraft in the future.