Abstract: Flying wing configuration aircraft possesses excellent aerodynamic and stealth characteristics. Traditional mechanical control surfaces can compromise its stealth profile, leading to a decrease in stealth performance. Active flow control (AFC) techniques effectively address the aforementioned drawbacks. First, a wind tunnel virtual flight test system, integrated with closed loop feedback control, was constructed. The system is capable of simulating and actively controlling the flight attitude of a controlled aircraft model under both steady and unsteady incoming flow condition. Based on that, wind tunnel virtual flight tests of a flying wing configuration model with AFC were conducted, obtaining its three-axis attitude control characteristics under steady flow conditions. Results demonstrate that consistent and controlled pitch and roll moments can be generated through trailing edge circulation control, while required yaw moment can be generated through wingtip reverse jets, achieving stable three-axis attitude control of a flying wing aircraft. Particularly, when controlling longitudinal attitude of the model with pitch circulation control, the generated pitch moment is linearly correlated with jet momentum coefficient. Furthermore, a closed loop control strategy for gust load alleviation based on model longitudinal attitude feedback was proposed. The stability enhancement ability of AFC for flying wing configuration model under gust disturbance was validated. Additionally, it was further discovered that the effectiveness of stability enhancement control is jointly determined by the intensity of the jet applied for control and the phase relationship between the control signal and the gust disturbance.

Key words: wind tunnel virtual flight test, active flow control, gust, attitude control, flying wing configuration