基于环量控制的无尾飞翼俯仰和滚转两轴无舵面姿态控制飞行试验  

Rudderless attitude control flight test based on circulation control of tailless flying wing in pitch and roll axes

作　　者：张刘[1] 黄勇[2] 陈辅政[1] 朱正龙 郭天豪 姜裕标[1] 周铸[2] ZHANG Liu;HUANG Yong;CHEN Fuzheng;ZHU Zhenglong;GUO Tianhao;JIANG Yubiao;ZHOU Zhu(Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心低速空气动力研究所,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《航空学报》2023年第18期70-79,共10页Acta Aeronautica et Astronautica Sinica

摘　　要：环量控制通过驱动压缩空气射流产生虚拟舵面实现无舵面飞行控制,显著提高低可探测性。基于无尾飞翼布局无人机,提出基于激励器终端压力反馈的闭环控制策略,自主开发机载多通道闭环控制射流作动系统,并与飞行控制系统进行融合,实现基于主动射流的姿态闭环控制,通过60 m/s巡航速度下飞行试验,定量研究了环量控制用于俯仰和滚转姿态控制能力。结果表明:环量激励器通道组合产生双向连续、稳定的俯仰和滚转控制力矩;射流作动系统响应延迟小于0.02 s,射流作动无人机姿态角速度响应时间小于0.02 s;俯仰环量激励器压比−1.025与升降舵−2.5°舵偏角产生的俯仰力矩相当,滚转环量激励器压比1.050与副翼2.0°舵偏角产生的滚转力矩相当,并分别实现纵向和横向无舵面姿态控制。The circulation control is efficient for rudderless flight control by driving the compressed air jet to generate a virtual rudder surface,which significantly improves low detectability.A closed-loop control strategy based on the termi⁃nal pressure feedback of the actuator is proposed,and an airborne multi-channel closed-loop control jet actuation sys⁃tem is independently developed,which was fused into flight control system,realized closed loop attitude control based on active jet.Based on the UAV with tailless flying wing configuration,in a fully autonomous flight control mode,the capability of circulation control for pitch and roll attitude control is quantitatively studied through the flight test at 60 m/s cruising speed.The results show that the combination of circulation actuator channels is available for bidirectional con⁃tinuous and stable control of pitch and roll control torque.The results also show that the response delay of the jetactuation system is less than 0.02 s,the response time of the jet-actuated UAV at the attitude angle velocity is less than 0.02 s;the pressure ratio−1.025 of the pitch circulation actuator is equivalent to the pitching moment generated by the elevator at−2.5°rudder angle,and the pressure ratio 1.050 of the roll circulation actuator is equivalent to the rolling moment generated by the aileron at 2.0°rudder angle,so as to realize rudderless attitude control in longitudinal and lateral attitude respectively.

关 键 词：环量控制 主动流动控制 飞行试验 飞翼 闭环控制 射流作动系统 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]