针对飞翼布局在隐身约束下依赖开裂式阻力舵进行航向控制所带来的机械结构重量大、低速工况舵效低、力矩跨轴耦合严重等问题，本文提出了一种创新的基于分布式射流舵的航向控制方法，不同于现有主动流动控制多以调节动量系数作为主要控制策略，所提出的分布式射流舵可在保持不变动量系数的条件下快速改变射流偏转组合方式以形成不同的偏航控制方案进而实现偏航力矩的离散可调输出。基于风洞实验建立分布式射流舵机翼模型，根据航向控制需求提出六种偏航控制方案，对比研究开裂式阻力舵与分布式射流舵在不同控制方案下的控制效果与跨轴耦合特性，并结合PIV技术对射流舵开启前后的尾缘流场结构进行定量分析。研究结果表明，本文提出的分布式射流舵最优偏航控制方案在-6°~6°迎角范围内产生的阻力超过开裂式阻力舵80°偏转效果，产生的偏航力矩大于开裂式阻力舵60°偏转效果，且在-6°~14°迎角范围内的平均滚转力矩增量为4.38%，相较于开裂式阻力舵减小了力矩跨轴耦合。流场分析表明，射流舵在翼面上形成了类似虚拟鼓包结构的凸起，对来流形成了阻挡效应，是产生阻力和偏航力矩的主要原因之一。该射流舵具有辅助或取代开裂式阻力舵的潜力，可为先进无舵面飞行器航向控制提供技术支撑。

To address the large mechanical weight, poor low-speed control effectiveness, and severe cross-axis coupling caused by yaw control of stealth-constrained flying wings using split-drag rudders, this paper proposes an innovative distributed jet-rudder yaw-control method. Unlike existing active flow-control approaches that primarily regulate the momentum coefficient, the proposed system maintains a constant momentum coefficient while rapidly switching jet-deflection combinations to form different yaw-control schemes and achieve discretely tunable yaw-moment outputs. A wind-tunnel wing model with distributed jet rudders was built, and six yaw-control schemes were designed. The control effectiveness and cross-axis coupling of the distributed jet rudder and split-drag rudder were compared, and particle image velocimetry (PIV) was used to quantify trailing-edge flow structures before and after actuation. Results show that, over angles of attack from ?6° to 6°, the optimal jet-rudder scheme yields a drag increment exceeding that of an 80°-deflected split-drag rudder and a yawing moment larger than that of a 60°-deflected split-drag rudder. Over ?6° to 14°, the mean rolling-moment increment is 4.38%, indicating reduced coupling. Flow analysis shows a “virtual hump” induced by the jet rudder blocks the incoming flow, contributing to drag and yawing-moment generation. The distributed jet rudder can potentially assist or replace split-drag rudders for yaw control of advanced tailless aircraft.