低旋鸭式弹道修正火箭弹控制力与控制方法研究

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。

Control force and control method of low-spin trajectory-corrected rocket with canards

The mechanism of control force is analyzed and an advanced canard deflection method is provided for the trajectory-corrected rockets with canards in a single channel.The system structure and operating principle of the trajectory-corrected rockets were briefly introduced.In accordance with projectile rolling characteristic, the control components of pitching plane and yawing plane were expressed based on periodic average method.Then the turnaround times and phase point were chosen on account of periodic average control force principles.To reduce the distraction from canard deflection and to maintain stability, the zero-position transition method was applied to canards deflection control.The final control force is provided with sinusoidal control method, which has greater correction capability.At last, with hardware in the loop simulation, the sinusoidal control method is verified to be feasible and effective and it can achieve well response rate and high control precision.The study provides theory and technology support to future guidance and control system design.