微型扑翼飞行器非定常运动对平尾的影响  

Influences of Flapping Wing Micro Aerial Vehicle Unsteady Motion on Horizontal Tail

作　　者：杨茵[1] 李栋[1] 张振辉[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《航空学报》2012年第10期1827-1833,共7页Acta Aeronautica et Astronautica Sinica

摘　　要：以西北工业大学自行研制的微型扑翼飞行器ASN211为研究对象,利用其简化的二维扑翼及平尾串列翼模型进行了非定常数值模拟,分析了扑翼俯仰运动及沉浮运动对平尾气动性能的影响。在数值模拟模块中,模型的俯仰运动及沉浮运动由动网格技术实现。通过计算流体力学(CFD)软件Fluent对此非定常流场进行数值计算,重点研究了扑翼非定常运动尾流对平尾气动效率的影响。定常状态与非定常时均条件下平尾升力曲线的对比分析表明,扑翼的非定常运动能够增大平尾的失速迎角及最大升力系数,因而使平尾的失速特性得到改善。By unsteady numerical simulating, this paper investigates the aerodynamic performance influence on the horizon- tal tail caused from flapping wing＇s pitching and plunging of a two dimensional model which is a flapping wing and horizontal tail combination in tandem model. We use the dynamic mesh technology to achieve flapping wing＇s pitching and plunging in the numerical simulation part. This two airfoils combination is simplified from a micro flapping wing aerial vehicle ASN211, which is developed independently by Northwestern Polytechnical University. We analyze the impact of the aerodynamic effi- ciency on the horizontal tail from flapping wing unsteady wake through the unsteady flow field calculation by the computational fluid dynamics software Fluent. By comparing the lift curves both in the steady state and time average unsteady state, we can conclude that the flapping wing＇s unsteady motion can enhance stalling angle and maximum lift coefficient of the horizon- tal tail, and hence improve the horizontal tail＇s stall features.

关 键 词：微型扑翼飞行器 非定常运动 动网格 平尾 失速 

分 类 号：V225.1[航空宇航科学与技术—飞行器设计]