论文部分内容阅读
设计确定一种可倾转翼梢小翼无人机总体基本参数,尾翼采用倒V型布局。在翼梢小翼倾转角从-60°~+90°内取6个角度,建立无人机相应几何和有限元网格模型。基于CFX软件,在迎角-3°~+27°范围,进行其低速流场纵向气动力特性数值仿真。结果表明:通过翼梢小翼倾转可增大无人机失速迎角,提高俯冲机动性。当迎角3°和小翼倾转角0°时,有利于巡航飞行并能获得最大续航时间。迎角大于18°后,小翼向上倾转可使无人机纵向稳定性增强。通过改变翼梢小翼倾转角,无人机可满足多工况、多任务的飞行需求。
Design to determine a total tilt wing winglets UAV overall basic parameters, the inverted V-shaped tail layout. In winglets tilt angle from -60 ° ~ + 90 ° take 6 angles, the establishment of UAV corresponding geometry and finite element mesh model. Based on the CFX software, numerical simulation of longitudinal aerodynamic characteristics of low velocity flow field was carried out in the range of -3 ° ~ + 27 ° angle of attack. The results show that the inclination angle of UAV can be increased by tilting wingtip and the dive maneuverability can be improved. When the angle of attack 3 ° and winglet tilt angle of 0 °, is conducive to cruise flight and get the maximum life time. After the angle of attack is greater than 18 °, the winglets tilt upward to enhance the longitudinal stability of the UAV. By changing the wingtip tilt angle, the UAV can meet the needs of multi-mission and multi-mission flight.