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31m,有效提高了火箭精度。
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.
出处
《计算机测量与控制》
2016年第5期132-134,共3页
Computer Measurement &Control
关键词
制导火箭弹
落点预测
修正
仿真
guided rocket
impact point predication
correction
simulation
