面向平飞姿态的四旋翼无人机机身造型设计  

Four-rotor UAV fuselage design for level flight attitude

作　　者：李洒 杨建明[1] 巩超 LI Sa;YANG Jianming;GONG Chao(School of Design&Arts,Beijing Institute of Technology,Beijing 100081)

机构地区：[1]北京理工大学设计与艺术学院,北京100081

出　　处：《机械设计》2025年第2期186-192,共7页Journal of Machine Design

摘　　要：为改进某型四旋翼无人机在平飞状态下的气动性能,提出一种基于升力体形态的无人机机身造型方案。采用对比试验方法,基于不同轮廓特征构建机身造型差异化方案,采用CFD数值模拟技术对设计方案进行分析与选型。在四旋翼无人机结构基础上,以NACA4415翼型模板构建机体造型的侧向轮廓,并分别以钝形和尖形翼缘两种造型特征构建了8种机身方案;采用CFD数值模拟技术对各设计方案的升力、阻力和升阻比等气动参数进行模拟计算,对比分析并筛选最佳方案。结果表明:最佳方案比原型机阻力系数减小了约52.8%,升力、阻力及俯仰力矩在特定迎角范围内具有线性变化特征,研究结果为改善旋翼无人机的气动造型进而提高其空气动力学性能提供参考。In order to improve the aerodynamic performance of a four-rotor UAV at level flight,an aerodynamic modeling scheme for UAVs was proposed based on lifting body shape.A comparative test method was used to construct models based on different contour features.Computational fluid dynamics numerical simulation technology was used to performed design schemes analysis and models selection.Based on the four-rotor UAV’s structure,the side view’s outline was constructed with the NACA4415 airfoil template.Eight models were created based on two morphological characteristics:blunt flange and pointed flange.Fluent software was used to simulate and analyze the aerodynamic performance of the models and filter the optimal solution.The results showed that the optimal scheme reduced the prototype’s drag coefficient by about 52.8%.The lift,drag,and pitching moment showed a linear gain in the specific Angle range.This improved the aerodynamic performance of rotary-wing UAV’s and provided references for the aerodynamic modeling design of the rotary wing UAV.

关 键 词：旋翼无人机 CFD 计算机辅助设计 气动造型 

分 类 号：V221.92[航空宇航科学与技术—飞行器设计] TB472[一般工业技术—工业设计]