When the canard-controlled missile is conducting roll control, the asymmetric downwash induced by the canard impacts on the fins and produces a reverse rolling moment, resulting in the aerodynamic coupling between the canards and the fins. The rolling coupling can cause the reduction and even failure of the missile roll control. However, the current rolling decoupling methods always have adverse effects on the lift-drag ratio or flight stability of the missile. Based on the numerical simulation, this paper proposes a new method to reduce the roll coupling by adding a jet system between the canards and the fins. The effect of jet control was obtained under different freestream conditions. The influence of jet control factors on the missile aerodynamic characteristics was investigated and analyzed. The outcomes demonstrate that the jet control can effectively decrease the roll coupling between the canards and the fins, and eliminate the reverse rolling problem in most cases. With the same mass flow rate, the control effect is better at lower Mach number. Jet location and jet mode have a higher influence on the control effect. An optimal mass flow rate exists for the best control efficiency. This decoupling method is simple in structure and can reduce the side force and yawing moment without destroying the lift-drag ratio.

当由卡纳德控制的导弹进行侧倾控制时，由卡纳德引起的不对称下降冲洗会冲击鳍片并产生反向滚动力矩，从而导致卡纳德鳍与鳍片之间的气动耦合。滚动耦合会导致导弹侧倾控制的减少甚至失败。然而，当前的滚动解耦方法总是对导弹的升阻比或飞行稳定性产生不利影响。在数值模拟的基础上，本文提出了一种新的方法，即通过在翼型和翼型之间增加射流系统来减少侧倾耦合。在不同的自由流条件下获得了射流控制的效果。研究并分析了射流控制因素对导弹气动特性的影响。结果表明，射流控制可以有效地减少鸭翼和鳍片之间的侧倾耦合，并在大多数情况下消除了反向侧倾问题。在相同的质量流量下，较低的马赫数下控制效果更好。喷射位置和喷射模式对控制效果有较大影响。存在最佳质量流量以获得最佳控制效率。这种解耦方法结构简单，可以减小侧向力和偏航力矩，而不会破坏升阻比。存在最佳质量流量以获得最佳控制效率。这种解耦方法结构简单，可以减小侧向力和偏航力矩，而不会破坏升阻比。存在最佳质量流量以获得最佳控制效率。这种解耦方法结构简单，可以减小侧向力和偏航力矩，而不会破坏升阻比。