基于CFD方法的垂直起降飞行器气动设计与分析  

Aerodynamic Design and Analysis of VTOL UAV Based on CFD Method

作　　者：赵楠 张志强[1] 孙巍伟[1] ZHAO Nan;ZHANG Zhi-qiang;SUN Wei-wei(Mechanical Electrical Engineering School,Beijing Information Science and Technology University,Beijing 100192)

机构地区：[1]北京信息科技大学机电工程学院,北京100192

出　　处：《液压与气动》2023年第4期132-140,共9页Chinese Hydraulics & Pneumatics

基　　金：北京市教委科研计划科技一般项目(KM2020 11232011)。

摘　　要：设计了一种复合式动力布局的垂直起降(vertical takeoff and landing, VTOL)飞行器,该飞行器采用无尾三角翼气动布局,静稳定设计,在其处于固定翼模式的情况下,使用CFD方法,基于Standard k-ε湍流模型对其进行了仿真分析。获得了在一定范围的迎角下飞行器的气动参数曲线以及升阻力情况,为该飞行器结构设计及控制系统设计提供了依据。仿真结果表明,该飞行器具有较小的阻力系数,且在最大升阻比附近的动态范围较宽,尤其适合高速飞行的场合。俯仰力矩几乎为0,无需平尾配平俯仰力矩,降低了控制系统的设计难度。飞行器整体设计布局合理,气动效率较高。A composite power layout VTOL UAV was designed.This vehicle adopts a tailless delta wing aerodynamic layout with a static stable design.A CFD method is used to simulate the UAV in fixed-wing mode based on the Standard k-εturbulence model.The aerodynamic parameter profiles and the lift drag of the UAV under a certain range of head angle are obtained,which provide a basis for the structural design and control system design of the UAV.The simulation results show that the UAV has a small drag coefficient and a wide dynamic range near the maximum lift-to-drag ratio,which is especially suitable for high-speed flight.The pitching moment is almost zero,and there is no need to level the pitching moment with a flat tail,which reduces the design difficulty of the control system.The overall design layout of the aircraft is reasonable and the aerodynamic efficiency is high.

关 键 词：垂直起降 飞行器 CFD FLUENT 气动特性 涵道发动机 

分 类 号：TH138[机械工程—机械制造及自动化] V279[航空宇航科学与技术—飞行器设计]