带升力风扇飞翼布局无人机过渡飞行气动特性研究  

Study on Aerodynamics Performance of Lift-fan UAV in Flying Wing Configuration in Transition Flight

作　　者：张炜[1] 张引妮[1] 蒋汉杰[2] 李慧 

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国航空工业集团公司第一飞机设计研究院,西安710089 [3]中航飞机股份有限公司研发中心,汉中723000

出　　处：《航空工程进展》2014年第2期193-200,共8页Advances in Aeronautical Science and Engineering

摘　　要：带升力风扇飞翼布局无人机除了具备飞翼机的优点外,还兼具短距/垂直起降功能,研究其过渡飞行阶段的气动特性是建立其飞行动力学模型的基础。对带升力风扇飞翼布局无人机的过渡飞行阶段进行气动仿真,分析升力、阻力和力矩随速度和迎角变化的特性,并在某定常流下对该布局飞机的流动机理进行研究,针对气流分离提出控制方法。结果表明:来流速度增大时,升力值持续增大,阻力增加,低头力矩增大;在相同来流速度下,迎角增大,升力随之增加且外段翼是其升力的主要来源,阻力先减小后增大,较常规平飞状态下有较大的抬头力矩;控制气流分离的两种改进方法是有效可行的。The lift-fan UAV in flying wing configuration not only has the advantages of the flying wing, but also can be capable of short distance/vertical takeoff and landing（S/VTOL）. Study on its aerodynamic performance is the foundation for building the dynamic model of flight. The lift-fan UAV performance in transition stage is studied by aerodynamic simulation, and the characteristics of lift, drag and moment with the changes of the ve- locity and angle of attack are analyzed. Aiming at the airflow separation, some control methods are presented. Study shows that the lift, drag, and nose-down moment increase with the increasing of velocity. In the same ve- locity, with the angle of attack increased, the lift is increasing and the outer wing is the main source to get the lift. The drag is decreasing first and then increasing. In comparison with the normal steady flight, the nose-up moment is much higher. Besides, the two control methods to improve the fluid separation are simple and effec- tive.

关 键 词：升力风扇 飞翼布局 无人机 气动特性 流场 分离控制 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]