| 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(中文),2026,36(7):731~741 |
| 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 |
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| DOI：10. 3772 / j. issn. 1002 - 0470. 2026. 07. 007 |
| 中文关键词: 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 |
| 英文关键词: aerodynamic efficiency, new π wing layout, wingtip active drag reduction technology, zero rudder plane flight control technology, rise to resistance ratio |
| 基金项目: |
| 作者 | 单位 | | 王耀坤* | （*北京航空航天大学航空科学与工程学院北京 100191）
（**北京航空航天大学工程实践与创新中心北京 100191） | | 韦嘉宁* | | | 邱玉婷** | | | 谢林博* | |
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| 中文摘要: |
| 油动无人机气动效率的提升成为当前研究的热点。本文设计了一种新型π翼布局零舵面无人机的技术验证机，旨在通过新的布局形式和创新技术提升常规油动无人机的气动效率。验证机采用新型π翼布局，前后两对平直翼共同提供正升力，增大升阻比；在前后双翼的翼尖处安装电机，驱动螺旋桨转动，提供飞行所需的动力，采用翼尖主动减阻技术，根据不同飞行阶段产生不同强度的滑流，能主动削弱翼尖涡流，减少翼尖气流下洗，进一步提升其气动效率。此外，验证机还采用零舵面飞行控制技术，利用翼尖电机驱动螺旋桨实现差速转动，产生操纵力矩进行姿态控制，实现了去舵面化设计，避免舵面操纵产生的附加阻力，进一步提升了气动效率。经过计算校核、气动仿真实验、地面试验和飞行试验验证，该验证机在飞行状态上保持正常，最大起飞重量为6.5kg，最大飞行速度可达60km·h-1，最大升阻比在17~18之间，是同等重量级常规无人机升阻比的1.5倍，显著提升了气动效率。该验证机的布局和创新技术有望应用于未来无人机的设计中。 |
| 英文摘要: |
| 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 technologies. The demonstrator adopts a new π-wing layout, with two pairs of straight wings at the front and rear providing 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 technology 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 efficiency. After calculation verification, aerodynamic simulation experiments, ground tests and flight tests, the demonstrator remains normal in flight state, with a maximum take-off weight of 6.5kg, a maximum flight speed of 60km·h-1, and a maximum lift-drag ratio of 17~18, which is 1.5 times that of conventional UAVs of the same heavyweight, significantly improving aerodynamic efficiency. The layout and innovative technology of the demonstrator are expected to be applied to the design of future drones. |
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