Virtual flight test for three-axis decoupling fluidic flight control of tailless flying wing

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.