为研究单通道导弹的舵面控制方法与达到有效控制的转速要求,建立了不同舵面控制律的数学模型,推导出工程化应用方法。采用数字仿真方式验证舵面控制律模型的正确性,通过给出一个阶跃指令,分析弹体在不同舵面控制律下的响应情况。为得到有效控制条件下的转速要求,设置导弹模型的不同转速,对比相应的弹体阶跃响应。结果表明:推导出的舵面控制律能够有效的响应控制指令且最低转速与弹体频率成正相关。

The relationship between actuator effective control and rotation rate of single-channel spinninging missile body was studied. The mathematic model of the actuator control was built, and the actual deflection angle of single-channel missile was deduced by the effect actuator instructions equivalence. The method proposed by this paper was applied to realistic dynamics model of single-channel rolling airframe. By giving a step command, the missile response was analyzed to get the lowest speed of body that reaches the stability control with the different actuator control law. The different missile response was analyzed by the different rotation rate for getting the minimum speed which has stability control. The simulation results show that actuator effective control is Effective and the speed is positively correlated with missile frequency for the stability control.