双通道控制旋转导弹舵面控制律研究

Research on Dual-Actuator Control Law of Rolling Airframe Missile

为解决导弹总体设计中亚跨速稳定性和超声速机动性不能兼顾的问题,对双通道控制旋转导弹舵面控制律进行了研究。分析了正弦、Bang-Bang、梯形和饱和正弦等控制律的原理与特点,给出了各自的等效舵偏角及其相应等效控制力的数学模型。采用基于两对舵面配合控制方式,给出了上述4种控制律的统一表示形式。讨论了两对舵配合控制方式的影响及工程可实现性,发现两对舵面相位差固定时,其等效控制力的方向由舵面1的相位决定,大小由其最大舵面偏角和特征函数决定,在工程中易实现;两对舵面相位差可变时,等效控制力的大小和方向需由控制舵1的相位和两对舵的相位差共同决定,考虑的变量更多,设计难度大,舵机系统复杂,难以实现小型化设计。仿真结果表明:采用基于两对舵面配合控制的旋转弹双通道控制方式,通过改变导弹舵面控制律,能有效提高导弹的操纵效率,在保证弹体静稳定性的同时增强导弹的机动能力,有效解决了传统旋转导弹总体设计中两者难以兼顾的难题。

To solve the problem that the stability and maneuverability could not be balanced in the missile overall design,the actuator control law of rolling airframe missile with dual-channel was studied in this paper.The principle and characteristics of sinusoidal control law,Bang-Bang control law,trapezoid control law and saturated sinusoidal control law were analyzed.The mathematical models of equivalent angle of rudder deflection and relevant equivalent control force were given.The dual-actuator was adopted which the operation was coupled.The uniform representation of the four control laws was presented.The effect of fitting-in control way of the dual-actuator and the implementation in engineering were discussed.It found that the direction of the equivalent control force was determined by the phase of actuator one and its amplitude was determined by the maximum angle of rudder deflection and characteristic function when the phase difference between the two actuators was not changed,and the direction and amplitude of the equivalent control force were determined by the phase of actuator one and the phase difference between the two actuators when the phase difference between the two actuators was changed.The more variables should be considered in the later situation,in which the design was difficulty,the actuator system was complicated and miniaturization design was not easy to be realized.The simulation results show that the control efficiency can be improved by changing control law of actuators using control method based on dual-actuator for rolling airframe missile,which improve good stability and maneuverability of the missile.The contradiction of rolling airframe missile design between stability and maneuverability in traditional way can be solved effectively.