气动推力矢量无舵面飞翼的飞行实验

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。 

Flight test of a fluidic thrust vectoring flying wing without rudder

In order to control the flying wing pitching and rolling without rudder, the layout named“single engine-inverted Ⅴ-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.