飞翼布局飞行器追求良好的气动性能、隐身性能。但传统机械舵面会破坏隐身外形，并且在中等攻角即出现舵效降低，易导致飞机失稳、失控，而主动流动控制技术能够有效解决上述弊端。构建了集成闭环反馈主动流动控制的风洞虚拟飞行试验系统，可在风洞环境中实现定常来流、非定常来流下受控模型飞行姿态模拟与主动调控。利用该系统，开展了飞翼布局主动流动控制风洞虚拟飞行试验，获得了定常来流条件下主动流动控制技术对飞翼布局三轴姿态控制规律。试验结果表明，基于后缘俯仰、滚转环量控制与翼尖反向射流能够分别产生规律可控的俯仰、滚转、偏航姿态控制力矩，实现飞翼布局三轴姿态的稳定控制。特别的，采用俯仰环量控制对模型纵向姿态控制时，产生的俯仰力矩与射流动量系数线性相关。提出了基于模型纵向姿态反馈的阵风载荷减缓闭环控制策略，验证了在阵风扰动下主动流动控制技术对飞翼布局的纵向增稳控制能力，进一步得出施加控制的射流强度、控制信号与阵风扰动的相位关系共同决定了增稳控制效果。

Flying wing configuration aircraft pursues excellent aerodynamic and stealth performance. However， traditional mechanical control surfaces can compromise its stealth profile and may lead to a decrease in control effectiveness at moderate angles of attack， potentially causing aircraft instability and loss of control. Active Flow Control （AFC） techniques effectively address the aforementioned drawbacks. In this study， a wind tunnel virtual flight test system， integrated with closed-loop active flow control， is constructed. The system is capable of simulating active flight attitude control of controlled model under both steady and unsteady incoming flow conditions. Utilizing this system， wind tunnel virtual flight tests of the flying wing configuration model with AFC are 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 the 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 is proposed. The stability enhancement ability of AFC for flying wing configuration model under gust disturbance is validated. Additionally， it is further discovered that the effectiveness of the 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.