无人飞行器外形布局设计及其气动特性计算分析  

Configuration Design and Aerodynamic Performance Analysis of an Unmanned Aerial Vehicle

作　　者：王允良[1] 高永[1] 侯志强[1] 

机构地区：[1]海军航空工程学院飞行器工程系

出　　处：《海军航空工程学院学报》2011年第4期361-364,374,共5页Journal of Naval Aeronautical and Astronautical University

基　　金：国家自然科学基金资助项目(50875024)

摘　　要：设计了一种新的无人飞行器气动外形布局，应用基于二次曲线的模线设计方法完成了飞行器气动外形建模，并对所建模型进行气动特性计算分析。将飞行器几何外形节点数据导入Gambit软件，生成气动特性计算所需的网格文件。应用Fluent软件，根据不同的飞行条件，选择合适的计算流体力学分析方法，对无人飞行器外形布局进行气动特性计算。主要讨论了在飞行马赫数为013、0．6和1.3时，对应不同飞行高度和迎角条件下飞行器的纵向气动特性，包括升力系数、阻力系数以及俯仰力矩系数。通过对计算结果的统计与分析，得出飞行器在不同飞行条件下的升阻比以及静稳定度，来判定其飞行性能以及飞行稳定性。经过计算与分析得出，所设计的飞行器外形布局符合飞行要求，并且具有良好的气动特性和稳定性。In this paper, a new configuration of an Unmanned Aerial Vehicle （UAV） was designed by conic lofting method and its aerodynamic performances were analyzed. The nodes of UAV geometry was generated and imported to Gambit software to build the grid file which was the foundation of aerodynamic computation. In terms of variant flight conditions, the suitable Computational Fluid Dynamics （CFD） methods were used to calculate the aerodynamic performances of UAV with Fluent software. The longitudinal aerodynamic performances of UAV with the speed of Mach 0.3, 0.6 and 1.3 were computed. The results including lift coefficient, drag coefficient and pitching moment coefficient at different heights were achieved. As a results were analyzed, the calculated data could show the high lift-to-drag ratio and longitudinal stability. In result, the configuration of UAV could satisfy the flying quality with favorable aerodynamic performances.

关 键 词：无人飞行器 气动布局设计 气动特性 计算流体力学 

分 类 号：V221.92[航空宇航科学与技术—飞行器设计]