摘要
为改善无人机起降和续航性能,对采用正弯度翼型的飞翼布局电动无人机进行计算研究。建立了无人机重量模型,机翼通过后掠、几何扭转以及襟翼、升降副翼的合理配置以减小纵向配平阻力,确定了一架航时为4 h的飞翼布局小型手掷电动无人机的总体参数。分别以航时和重量尺寸为算例目标,使用遗传算法对无人机总体参数进行优化。计算结果表明:相对于反弯度翼型,使用正弯度翼型的飞翼布局无人机能减小无人机重量和尺寸,延长留空时间。
To improve performance of taking-off, landing and endurance, the flying-wing electric-powered UAV based on cambered airfoil is studied. The mass model of UAV is presented. Longitudinal trimmed drag is reduced by the swept wing, geometrical twist as well as optimized dimension of flap and elevon. Configuration parameters of a hand-launched flying-wing electric-powered UAV based on 4 hours endur- ance are confirmed. Then, the configuration parameters are optimized using the genetic algorithm to max- imize the endurance and minimize size, respectively. In comparison with the flying-wing UAV with reflex airfoil, the mass and size with cambered airfoil are decreased. Meanwhile, UAV endurance is increased.
出处
《飞行力学》
CSCD
北大核心
2013年第1期33-36,41,共5页
Flight Dynamics
关键词
手掷电动无人机
飞翼布局
总体参数设计
hand-launched electric-powered UAV
flying-wing
configuration parameter design
