尾坐式超小型无人机的流体动力学仿真研究  

Fluid Dynamics Simulation Research on Tail-sitter Subminiature Unmanned Aerial Vehicle

作　　者：张志峰[1] 饶进军[1] 

机构地区：[1]上海大学机电工程与自动化学院,上海200072

出　　处：《机械制造》2011年第5期5-7,共3页Machinery

基　　金：国家自然科学基金资助项目(编号:50905103)

摘　　要：尾坐式无人机是一种采用尾坐式设计的具有垂直起降功能的无人机,该机不仅具有固定翼无人机飞行效率高、巡航速度快等优点,又有旋翼式无人机垂直起降和悬停的能力,具有很高的研究意义和应用价值。为了研究尾坐式无人机在尺寸超小型化和低雷诺数特定条件下的气动性能,利用商业CFD软件对其进行三维流体动力学数值模拟,获取无人机的主要气动特性,并对巡航速度条件下的升力系数、阻力系数等进行了分析研究,为无人机的整体优化做准备。The tail-sitter unmanned aerial vehicle （UAV） is a type of UAV with tail-sitter design as well as the function of vertical takeoff and landing （VTOL）. The vehicle not only has the advantages of high flight efficiency and cruising speed of fixed-wing UAV, but also the capabilities of VTOL and hovering of rotor-type UAV. All these advantages provide the tail- sitter UAV with research significance and high application value. To study the aerodynamic performance of the tail-sitter UAV under the specific conditions of subminaturization and low Reynolds number, the commercial CFD software was used to carry out a three dimensional numerical simulation of fluid dynamics. The main aerodynamic characteristics of UAV were acquired. Lift and drag coefficients, as well as other characteristics of UAV under certain cruising speed, were analyzed in order to prepare for the overall optimization of UAV.

关 键 词：计算流体力学尾坐式超小型无人机 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]