大展弦比飞翼布局飞机取消了垂尾和常规方向舵,通常采用大偏角的开裂式方向舵作为偏航操纵面。基于风洞试验数据,研究了开裂式方向舵的偏航操纵非线性、小偏角偏航舵效低、附加力效应显著和3轴操纵耦合等特性,并分析了其偏转对飞机气动特性和稳定特性的影响。总结了开裂式方向舵在各飞行任务阶段下的使用特点,如针对其小偏角偏航舵效低的特性,在对飞机隐身性能要求不高的飞行阶段,为保证能够迅速地产生足够的操纵效能,双侧均必须保持小偏角张开。最后从飞行控制设计控制分配应用的角度出发,为获得足够的操纵效能和充分发挥附加阻力的作用,得出了开裂式方向舵适合采用双侧独立偏转的方式和阻力优化控制分配的策略。
The high-aspect-ratio flying wing eliminates vertical tail and conventional rudder, and uses instead a split drag rudder with large deflection as its directional control surface. Based on wind tunnel test data, the control features of a split drag rudder is discussed, including its nonlinear yaw control, low directional control efficiency with small deflection, strong additional force effects and 3-axis coupling controls; and then the impact of the split drag rudder on the aerodynamic performance and stability features of the aircraft is analyzed. Application characteristics of the split drag rudder in every flight phase are summarized. For example, due to its low directional control efficiency with small deflection, the split drag rudder may maintain small deflection in some flight phases where the aircraft doesn't need high stealth performance so as to quickly generate enough control effectiveness. From the overview of flight control design and control allocation application, in order to provide enough control effectiveness and give full play to the feature of additional drag, it is concluded that it is suitable for the split drag rudder to adopt the both-side-independent-deflect mode and the strategy of optimized drag control allocation.
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