摘要
等离子体流动控制技术已经在流动控制领域成为热点和焦点。为了研究等离子体对于飞翼布局飞机稳定性的影响,本文研究中采用闭环飞行控制律对飞翼布局飞机模型的操纵舵面进行操控,同时增加等离子控制,对该模型飞机在失速迎角附近区域开展三自由度(3DoF)的虚拟飞行试验研究。结果表明,等离子打开后,在俯仰运动上,使得飞机俯仰振荡幅值变小,增快振荡衰减,在滚转运动上,对滚转角命令的跟随性变好;在偏航运动上,增加了偏航阻尼,改善了原来偏航运动的偏离问题。因此,等离子流动控制对于飞翼布局飞机在失速迎角附近的稳定性改善具有良好的效果,对未来等离子技术的实际应用提供了借鉴和指导。
Recently,the plasma actuation technique are the hot spots of active flow control research fields.In this paper,in order to research the influence of the plasma actuation to the stability of the flying wing configuration aircraft,the closed-loop filght control law is used to control the control surface of the wind tunnel test model.And adding the plasma actuation control method,the 3DOF virtual flight test was carried out near the stall angle of attack.The test results are shown,after the plasma used,for the pith motion,the pitch motion amplitude decreased and the attenuation speed are increased.For the roll motion,the follow ability of roll-instruction is better.For the yaw motion,the yaw damping is increased,and the yaw direction deviation problem is improved.Therefore,stability of the flying wing configuration aircraft can be improved by the plasma actuation near the stall angle of attack.The research in this paper provides reference for the practical application of plasma actuation technology in the future.
作者
尚祖铭
吴佳莉
牛中国
卜忱
Shang Zuming;Wu Jiali;Niu Zhongguo;Bu Chen(AVIC Aerodynamic Research Institute,Haerbin 150001,China;Aviation Key Laboratory of Aerodynamics for Low Speed and High Reynolds Number,Harbin 150001,China)
出处
《航空科学技术》
2019年第9期40-46,共7页
Aeronautical Science & Technology
关键词
等离子控制
飞翼布局
虚拟飞行
风洞试验
plasma actuation
flying wing configuration
virtual flight
wind tunnel test
