中等展弦比飞翼布局无人机后缘射流滚转控制  

Roll control of medium-aspect-ratio flying-wing UCAV based on trailing-edge jet

作　　者：邵帅 郭正[1] 贾高伟 陈清阳[1] 侯中喜[1] 张来平 SHAO Shuai;GUO Zheng;JIA Gaowei;CHEN Qingyang;HOU Zhongxi;ZHANG Laiping(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;National Innovation Institute of Defense Technology,Academy of Military Sciences,Beijing 100071,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]军事科学院国防科技创新研究院,北京100071

出　　处：《航空学报》2023年第10期49-59,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(61801495);湖南省科技创新计划项目(2021RC3077)。

摘　　要：飞翼布局飞行器有望依靠射流主动流动控制技术实现无舵面飞行以改善隐身特性,但鲜有针对中等展弦比(3~4.5)战术级飞翼的相关研究。本文为中等展弦比飞翼布局无人机设计环量控制激励器取代传统副翼,开展全机数值模拟和飞行试验研究,探究后缘环量控制射流的滚转控制能力。数值模拟使用压力入口边界并考虑射流动量贡献的气动力,实现对飞翼绕流和激励器内流耦合模拟和整机气动特性预测。数值模拟研究表明,射流的滚转控制能力随射流动量系数线性增长,且未产生显著的横航向或横纵向耦合力矩。飞行试验结果表明,环量控制激励器实现了平均滚转角速率25.5~26.7(°)/s,最大滚转角速率40.1(°)/s,最大滚转角83.9°的控制效果。With jet active flow control technologies,the flying-wing aircraft are expected to achieve flapless flight which can improve the stealth characteristics.However,little research has been done on the tactical flying-wing platforms with a medium aspect ratio(3-4).We design a Circulation Control Effector(CCE)to replace the ailerons of a medium-aspect-ratio flying-wing UCAV.Numerical simulations and flight tests of the demonstrator are conducted to in⁃vestigate the roll control effectiveness of the trailing-edge circulation control jet.In numerical simulations,the pressure inlet boundary is adopted,and the contribution of the jet momentum is also considered in the aerodynamic force calcu⁃lation.Then,the coupling simulation of the inner flow in the CCE and the outer flow over the flying-wing UCAV is real⁃ized,and the aerodynamic characteristics of the demonstrator are predicted.The simulation results show that with the increase of the jet momentum coefficient,the roll control capability increases almost linearly,with no obvious coupling yaw moment or pitch moment.The flight test results indicate that remarkable roll control effectiveness is achieved by the CCE,with the mean roll rate being 25.5-26.7(°)/s,the maximum roll rate 40.1(°)/s,and the maximum roll angle 83.9°.

关 键 词：主动流动控制 环量控制 飞翼布局 滚转控制 飞行试验 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]