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针对单通道鸭式弹道修正火箭弹,分析了控制力的产生原理,提出了一种新的舵偏控制方法。简述了弹道修正火箭弹的系统组成和工作原理;根据弹体滚转特性,采用周期平均法确定了弹体在俯仰通道和偏航通道的控制分量;基于周期平均力产生的原理,确定舵机换向的次数、换向相位的选择方法,提出了零位过渡的舵偏控制方法,减小舵机瞬时偏转带来的扰动和对稳定性的影响;对比修正能力,采用正弦舵偏控制方法,确定了控制力的最终算法。最后,通过半实物仿真试验验证,表明正弦舵偏控制方法具有很好的可行性和有效性,能够实现良好的响应速度和控制精度,为后续的制导控制设计提供了有效的理论和技术支持。
Aiming at the single-channel duel ballistic correction rocket, the generation principle of control force is analyzed and a new control method of helm bias is proposed. The system components and working principle of the ballistic correction rocket are briefly described. According to the rolling characteristics of the projectile, the periodic averaging method is used to determine the control components of the projectile in the pitch and yaw channels. Based on the principle of periodic average force generation, The number of machine commutation and the selection method of commutation phase, a method of steering partial deviation control with zero transition is proposed to reduce the disturbance caused by instantaneous deflection of steering gear and the influence on stability. Compared with the correction ability, Method, to determine the ultimate control of the algorithm. Finally, the simulation of semi-physical simulation shows that the sinusoidal steering partial control method is feasible and effective, and can achieve good response speed and control accuracy, which provides effective theoretical and technical support for the subsequent guidance control design.