旋转弹舵机控制滞后及其对策研究  

Study on Steering Engine Control Hysteresis and the Countermeasure of Spinning Missile

作　　者：陈利风[1] 李龙[1] 姚晓先[2] 

机构地区：[1]江苏自动化研究所,江苏连云港222006 [2]北京理工大学,北京100081

出　　处：《弹箭与制导学报》2017年第3期59-63,87,共6页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对旋转弹飞行过程中舵机控制滞后的难点,建立了控制滞后角的分析模型,重点研究了舵机、地磁陀螺和弹载计算机三方面导致滞后角的因素,给出了控制总滞后角计算方法。基于滞后与时间延迟的线性关系,提出了按滚转角速率补偿滞后角的算法,并进行了实验验证,实验结果表明其较好的解决了舵机控制滞后的问题,具有较高的工程应用价值。Aiming at the difficulty of the steering engine control hysteresis in the flight process of spinning projectile, a calculation method for controlling the total lagging angle was established by establishing an analysis model and the research on three components leading to lagging angle, which were steering engine, geomagnetic gyro and missile-borne computer. At last, the algorithm of compensating lagging angle according to the rate of roll angle was proposed and tested based on the linear relationship between hysteresis and time delay. The results showed that this method effectively solved the steering engine control hysteresis problem, and had high engineering application value.

关 键 词：旋转弹 控制滞后 滞后角 对策 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]