微型扑翼飞行器的气动建模分析与试验  

Aerodynamic Modeling and Analysis of Flapping-Wing MAV

作　　者：刘岚[1] 方宗德[1] 侯宇[1] 傅卫平[2] 吴立言[1] 

机构地区：[1]西北工业大学机电学院,陕西西安710072 [2]西安理工大学机械与精密仪器工程学院,陕西西安710048

出　　处：《航空动力学报》2005年第1期22-28,共7页Journal of Aerospace Power

基　　金：国防基础科研资助项目 ( K 180 0 0 60 10 9) ;西北工业大学博士创新基金资助项目 ( M0 1610 3 )

摘　　要：用计算流体力学的数值模拟方法研究了微扑翼飞行器的扑翼飞行的非定常空气动力学问题。在对昆虫扑翼飞行运动的仿生模拟基础上 ,对实际可飞的微扑翼飞行器的扑翼运动建立了三维翼型的运动学与空气动力学模型。利用任意拉格朗日欧拉 ( ALE)有限元方法求解出 N-S方程的数值解 ,证明简单扑翼布局所提供的升力足以克服微扑翼飞行器本身的重力使其飞行。在此基础上 ,分别计算并分析了拍动幅值、俯仰幅度以及扑翼频率等各种扑翼参数对升力的影响。最后 。The unsteady aerodynamics associated with flapping flight of flapping-wing Micro Air Vehicles (MAVs) was studied using computational fluid dynamics. A three-dimensional flapping wing model was established for the MAV, which mimicked biological locomotion, such as insect flight. The Arbitrary Lagrangian Eulerian (ALE) finite element method with ANSYS/CFD was used to solve the Navier-Stokes equations numerically. The solution proves that the leading-edge vortices could generate enough lift to support a typical flapping MAV. Based on the bionics aerodynamic model, the variations of different parameters such as flapping amplitude, pitching amplitude and flapping frequency of the MAV were studied. Finally, exploratory flapping wing wind-tunnel test and flight test prove, in certain degree, the feasibility of the method presented. The modeling method, as well as the conclusions is suitable for the design and analysis of flapping-wing MAVs.

关 键 词：航空、航天推进系统 微扑翼飞行器 仿生 计算流体力学 风洞试验 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]