In order to enhance the omnidirectional stealth and maneuvering control capability of tailless flying wings, the fluidic flight attitude control scheme that combines Fluidic Thrust Vectoring (FTV) yaw control and longitudinal and lateral Circulation Control (CC) is proposed to realize three-axis moment decoupling control. Constrained by the mass flow rate of 30 kgf (1 kgf = 9.8 N) thrust turbojet engine bleed air, the equivalent rudder deflection control variables of mass flow combination and jet pressure ratio are proposed respectively by adopting the circulation actuator design of co-directional FTV nozzle and convergent nozzle + backstep. A control model is established to form a 10-channel jet actuation system scheme, and is integrated with the flight control system of a tailless flying wing with a wingspan of 4 m and a medium aspect ratio of 100 kg to realize three-axis attitude closed-loop control based on fluidic flight control. Through wind tunnel force measurement and powered virtual flight test at 35 m/s wind speed, the control characteristics and effectiveness of CC and the attitude control performance of fluidic flight control are quantitatively studied. The results show that the incremental range of pitch moment coefficient generated by the jet with a mass flow rate of 37 g/s of the jet elevator is −0.01812 to 0.01848, and the CC efficiency is greater than 30; the incremental range of roll moment coefficient generated by the jet with a mass flow rate of 34 g/s of the jet aileron is −0.01485 to 0.01358; the fluidic flight control scheme based on compressor bleed air is first used to realize the fluidic flight of tailless flying wing with three-axis attitude control decoupling, at a maximum pitch rate of 19.2 (°)/s, a roll rate of 13.8 (°)/s, and a yaw rate of 5.4 (°)/s; the constructed 10-channel jet actuation system and gas supply pipeline have good robustness and anti-interference characteristics.

Fluidic Thrust Vectoring (FTV) is used for the yaw attitude control of tailless flying wing, which can significantly improve stealth performance, maneuverability and lateral/heading maneuverability. The FTV control scheme of co-directional secondary flow was designed based on a 30 kgf thrust turbojet engine, an equivalent rudder deflection control variable of Mass Flow Combination (MFC) was proposed, and a control model was established to form a FTV control system scheme, which was integrated with the flight control system of a 100 kg tailless flying wing with medium aspect ratio to achieve closed-loop control of the yaw attitude based on FTV. The heading stability augmentation and maneuvering control characteristics and time response characteristics of tailless flying wing by FTV were quantitatively studied through virtual flight test in a wind tunnel at a wind speed of 35 m/s. The results show that the control strategy based on MFC achieves bidirectional continuous and stable control of thrust vector angle in a range of ±11°, and the thrust vector angle varies monotonically with MFC; the co-directional FTV realizes bidirectional continuous and stable control of the yaw attitude of tailless flying wing, without longitudinal/lateral coupling moment. The increment of the maximum yawing moment coefficient is 0.0029, the maximum yaw rate is 7.55 (°)/s, and the response time of the yaw rate of the vectoring nozzle actuated by the secondary flow is about 0.06 s, which satisfies the heading stability augmentation and maneuvering control response requirements of the aircraft with statically unstable heading, and provides new control means for the heading rudderless attitude control of tailless flying wing.