制导火箭弹落点预测导引控制研究

Study on Course Correction for Guided Rocket Based on Impact Point Predication

摘要:

为了提高火箭弹攻击地面目标的精度,文中给出了一种基于落点预测的火箭弹导引方法；首先以某型火箭弹为例,建立了其运动方程组,然后简化处理弹道方程得到落点预测模型,设计了基于落点预测模型的导引律,最后建立了Simulink六自由度弹道仿真模型并进行了数字仿真验证；研究结果表明:落点预测模型有效,相比无控火箭,采用落点预测导引律后制导火箭CEP由231 m减小为31 m,有效提高了火箭精度。

Abstract:

To improve the precision of the rocket, a guidance method based on impact point predication was proposed. Firstly, the dynamics equations was built for a type of rocket, then impact point predication model was adopted to design guidance law,finally the six-degree-of-freedom trajectory simulation model in Matlab/Simulink was established and simulated. The result indicates that the trajectory model is efficient, and impact point predication mode is practicable. Compared with uncontrol rocket, CEP of guided rocket was minished from 231 m to 31 m through impact point predication guidance law, rocket precision was improved availability in improving the precision of rocket.