摘要
可垂降飞行器多采用旋翼与固定翼复合式和尾座式等垂降实现方式,但存在高亚音速或超音速飞行时阻力大、垂降过程中操作稳定性差等问题。为兼顾飞行器高亚音速飞行的低阻特性及可垂降的功能,基于滑盖翼垂降调姿的飞行器垂降控制方法,提出一种高亚音速可垂降折叠翼飞行器。基于Fluent建立飞行器的气动仿真模型,结合SST k-ω湍流模型对飞行器进行外流场模拟,分析不同飞行速度及迎角下的气动特性;对比滑盖翼未展开及展开过程的飞行器气动特性,研究滑盖翼对飞行器气动特性的影响。结果表明:所提出的可垂降折叠翼飞行器在亚音速时具有较好的气动特性;高亚音速飞行升阻比达到7.2,飞行器具有较佳气动特性;加装滑盖翼在飞行时对飞行器主翼面气流产生影响,进而影响飞行性能;垂降过程中滑盖翼展开未对飞行器气动特性产生明显影响。
The vertical landing aircraft often use such methods as the rotor and fixed wing composite and the tailstock to achieve vertical landing,but there are problems such as high resistance during high-subsonic or supersonic flight and poor operational stability during vertical landing.In this article,in order to balance the high-subsonic flight’s low drag characteristics and the aircraft’s vertical landing function,a vertical landing control method based on sliding-cover-wing vertical landing attitude adjustment is proposed for a high-subsonic vertical landing foldable wing aircraft.An aerodynamic simulation model is set up for the aircraft based on Fluent;combined with the SST k-ωturbulence model,efforts are made to simulate the aircraft’s external flow field and explore the aerodynamic characteristics at different flight speeds and with angles of attack.The aircraft’s aerodynamic characteristics during the non-deployment and deployment process of the sliding cover wing are compared,and the influence of the sliding cover wing on the aircraft’s aerodynamic characteristics is explored.The results indicate that the vertical landing foldable wing aircraft exhibits good aerodynamic characteristics at subsonic speeds;the lift-to-drag ratio of subsonic flight reaches 7.2,and the aircraft has better aerodynamic characteristics;the sliding cover wing affects the airflow on the aircraft’s main wing surface during flight,thereby affecting its flight performance;the deployment of the sliding cover wing during vertical landing doesn’t have a significant impact on the aircraft’s aerodynamic characteristics.
作者
张争争
胡明
张谋
赵德明
彭婉怡
朱梓扬
ZHANG Zhengzheng;HU Ming;ZHANG Mou;ZHAO Deming;PENG Wanyi;ZHU Ziyang(National and Local Joint Engineering Research Center for Reliability Analysis and Test of Mechanical and Electrical Products,Zhejiang Sci-Tech University,Hangzhou 310018;Aerospace Star Militarycivil Fusion Innovation Institute,Changsha 410299)
出处
《机械设计》
北大核心
2026年第2期26-36,共11页
Journal of Machine Design
基金
国家重点研发计划项目(2018YFB1308100)
国家自然科学基金项目(51375458)。
关键词
折叠翼
高亚音速
垂降飞行器
滑盖翼
气动特性
foldable wing
high subsonic
vertical landing aircraft
sliding cover wing
aerodynamic characteristic
