通过建立制导滚转火箭的力学模型,分析了射流元件执行机构射流力切换延迟时间对滚转制导火箭精度的影响。由于存在实时变化的射流力切换延迟时间,通过设定相位超前角可提高控制精度。相位超前角约为弹体转速和射流力切换延迟时间的乘积。对包含射流元件指令转换和射流元件动力学方程的制导火箭模型进行了仿真,结果表明,在射流元件指令中实时的增加相位超前角与传统的固定超前角相比,控制精度能够显著提高。

The effect of jet element switch time on the fall point accuracy of spinning missile was presented by a dynamic model. If the phase lead angle is added to the input commands of the jet element, the tracking precision of jet element is enhanced. The leading phase angle was obtained using the product of the switch time and the roll angular velocity. The six degree of freedom simulation was done with the dynamic model of the spinning missile which includes the transform functions of the jet element commands and the dynamic equations of the jet element. The simulation result shows that the guidance precision increases obviously when the leading phase angular changes according to the switch time instead of the fixed.