气动推力矢量无舵面飞翼的飞行实验
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摘要
为实现对无舵面飞翼姿态的控制,针对基本型旁路式双喉道气动推力矢量喷管提出了"单发倒Ⅴ双喷管"布局。随后对该布局的喷管进行测力实验,并且最终将其安装在飞行器上进行了成功试飞,并对采集到的飞行数据进行了分析。结果表明:喷管矢量角随喷管阀门开度基本呈线性变化,且无滞回性;安装该布局喷管的飞行器可以不通过舵面控制,仅仅依靠旁路式双喉道气动推力矢量喷管即可有效地控制飞行器姿态;对于所研究的飞行器,在滚转机动性方面,矢量控制与舵面控制效果相近,而对于俯仰机动性,矢量控制效果较弱;后续如果使用该布局喷管控制飞行器姿态时,应当增大两个喷管之间的夹角,将更适用于飞翼布局飞行器的操纵。
In order to control the flying wing pitching and rolling without rudder,the layout named "single engine-invertedⅤ-double nozzle"was proposed based on the basic bypass dual throat fluidic thrust vectoring nozzle.Then the nozzle of the layout was tested for the first time.Finally the aircraft installed with the layout nozzle had a successful test flight and the flight data were collected and analyzed.The results show that the vector angle varies linearly with the nozzle valve opening and the nozzle does not present hysteresis.The aircraft equipped with the layout nozzle can be controlled by the bypass dual throat thrust vectoring nozzle without the rudder.In the aspect of rolling maneuverability for the aircraft,the vector control is similar to the rudder.But for pitch maneuverability,the effect of vector control is weak.The angle between the two nozzles should be increased,making it more suitable for the control of flying wing aircraft.
In order to control the flying wing pitching and rolling without rudder,the layout named "single engine-invertedⅤ-double nozzle"was proposed based on the basic bypass dual throat fluidic thrust vectoring nozzle.Then the nozzle of the layout was tested for the first time.Finally the aircraft installed with the layout nozzle had a successful test flight and the flight data were collected and analyzed.The results show that the vector angle varies linearly with the nozzle valve opening and the nozzle does not present hysteresis.The aircraft equipped with the layout nozzle can be controlled by the bypass dual throat thrust vectoring nozzle without the rudder.In the aspect of rolling maneuverability for the aircraft,the vector control is similar to the rudder.But for pitch maneuverability,the effect of vector control is weak.The angle between the two nozzles should be increased,making it more suitable for the control of flying wing aircraft.
引文
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[3]郭亚东.航母上的“战斗轰炸机”:美X-47B舰载无人机样机正式亮相[J].环球军事,2009(9):58-59.
[4]张翼麟,张绍芳.神经元无人机成功完成首飞[J].飞航导弹,2012(12):1.
[5]魏国福,周军,邢娅.欧洲神经元无人攻击机发展历程[J].飞航导弹,2013(8):23-26.
[6]李斌,张子彦.推力矢量控制对飞机操稳特性的影响[J].飞行力学,1998,16(2):36-40.LI Bin,ZHANG Ziyan.The effect of thrust vectoring on aircrafts stability and controllability[J].Flight Dynamics,1998,16(2):36-40.(in Chinese)
[7]王立峰,张津,唐海龙.推力矢量控制飞行的仿真研究[J].航空动力学报,2000,15(4):427-430.WANG Lifeng,ZHANG Jin,TANG Hailong.Simulation of vector thrust control flight[J].Journal of Aerospace Power,2000,15(4):427-430.(in Chinese)
[8]连永久.射流推力矢量控制技术研究[J].飞机设计,2008,28(2):19-24.LIAN Yongjiu.Fluidic thrust vectoring techniques research[J].Aircraft Design,2008,28(2):19-24.(in Chinese)
[9]FIELDING J,LAWSON C,RUI M P,et al.Design,build and flight of the DEMON demonstrator UAV[R].AIAA-2011-6963,2011.
[10]MASON M S,CROWTHER W J.Fluidic thrust vectoring for low observable air vehicles[R].AIAA-2004-2210,2004.
[11]肖中云,江雄,牟斌,等.流体推力矢量技术研究综述[J].实验流体力学,2017,31(4):8-15.XIAO Zhongyun,JIANG Xiong,MOU Bin,et al.Advances influidic vectoring technique research[J].Journal of Experiments in Fluid Mechanics,2017,31(4):8-15.(in Chinese)
[12]韩杰星,顾蕴松,龚东升,等.一种楔形多控制孔式流体推力矢量喷管:CN107084070A[P].2017-08-22.
[13]李明.双喉道气动矢量喷管特性研究[D].南京:南京航空航天大学,2011.LI Ming.Research on dual throat fluidic vectoring thrust nozzle[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2011.(in Chinese)
[14]李明,徐惊雷,黄顺洲,等.旁路式双喉道无源矢量喷管:CN102434315A[P].2012-05-02.
[15]顾瑞.新型双喉道气动矢量喷管机理与关键技术研究[D].南京:南京航空航天大学,2013.GU Rui.Research on the key technology of new dual throat fluidic vectoring thrust nozzle[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2013.(in Chinese)
[16]范志鹏,徐惊雷,郭帅.次流通道对双喉道气动矢量喷管的性能影响研究[J].推进技术,2014,35(9):1174-1180.FAN Zhipeng,XU Jinglei,GUO Shuai.Effects of secondary injection pipe on dual throat nozzle thrust vectoring performances[J].Journal of Propulsion Technplogy,2014,35(9):1174-1180.(in Chinese)
[17]谭慧俊,陈智.二维双喉道射流推力矢量喷管的数值模拟研究[J].航空动力学报,2007,22(10):1678-1684.TAN Huijun,CHEN Zhi.A computational study of 2-D dualthroat fluidic thrust-vectoring nozzles[J].Journal of Aerospace Power,2007,22(10):1678-1864.(in Chinese)
[18]梁德旺.流体力学基础[M].北京:航空工业出版社,2009.