高技术通讯2026，Vol.36Issue(7)：731-741,11.DOI:10.3772/j.issn.1002-0470.2026.07.007
新型π翼布局零舵面技术验证机的教学设计与实践
Teaching design and experiment of a novel π-wing layout zero rudder surface UAV
摘要
Abstract
The improvement of aerodynamic efficiency of oil-powered UAVs has become a hot topic of current research.In this paper,a new technical demonstration machine for π-wing layout zero-rudder UAV is designed,aiming to improve the aerodynamic efficiency of conventional oil-powered UAV through new layout forms and innovative tech-nologies.The demonstrator adopts a new π-wing layout,with two pairs of straight wings at the front and rear provi-ding positive lift and increasing the lift-drag ratio.Motors are installed at the wingtips of the front and rear wings to drive the propellers to rotate and provide the power required for flight,and the wingtip active drag reduction tech-nology is used to generate slip streams of different intensities according to different flight stages,which can actively weaken the wingtip vortex,reduce the wingtip airflow downwash,and further improve its aerodynamic efficiency.In addition,the demonstrator also adopts zero rudder plane flight control technology,using wingtip motors to drive the propeller to achieve differential rotation,generate control torque for attitude control,realize the de-rudder surface design,avoid the additional resistance caused by rudder surface manipulation,and further improve aerodynamic ef-ficiency.After calculation verification,aerodynamic simulation experiments,ground tests and flight tests,the dem-onstrator remains normal in flight state,with a maximum take-off weight of 6.5 kg,a maximum flight speed of 60 km·h-1,and a maximum lift-drag ratio of 17~18,which is1.5 times that of conventional UAVs of the same heavyweight,significantly improving aerodynamic efficiency.The layout and innovative technology of the demon-strator are expected to be applied to the design of future drones.关键词
气动效率/新型π翼布局/翼尖主动减阻技术/零舵面飞行控制技术/升阻比Key words
aerodynamic efficiency/new π wing layout/wingtip active drag reduction technology/zero rud-der plane flight control technology/rise to resistance ratio引用本文复制引用
王耀坤,韦嘉宁,邱玉婷,谢林博..新型π翼布局零舵面技术验证机的教学设计与实践[J].高技术通讯,2026,36(7):731-741,11.基金项目
国家自然科学基金(52472184)资助项目. （52472184）
