An optimization design of small rolling missile controller parameter based on genetic algorithms was developed.
提出了一种基于遗传算法的小型旋转弹控制器参数优化设计方法。
The mechanism of dynamic instability of rolling missile was analyzed by describing the dynamics of rolling missile as a closed loop with dynamic negative feedback.
将滚转导弹动力学系统描述为一个具有动态负反馈的闭环系统，分析了滚转导弹动态失稳的机理。
Considering the difference of the rolling missile and the non-rolling missile, the mechanism of rolling missile control force and the control theory of rolling missile was analyzed rigorously.
考虑到滚转导弹与非滚转导弹的不同，本文仔细分析了滚转导弹控制力的产生机理和滚转导弹的控制原理。
Based on the characteristics of rolling missile with double-channel control, the autopilot loop is transferred from body coordinate system to quasi-body coordinate system after a rolling transfer.
根据双通道控制旋转导弹的特点，通过旋转变换，将弹体坐标系下的自动驾驶仪回路变换到准弹体坐标系下，并比较了与倾斜稳定导弹标准自动驾驶仪的区别。
The Rolling Airframe Missile Block 2 is a kinematic and sensor upgrade to the company’s Rolling Airframe Missile Block 1.
RAMBlock2是一种动能弹，和Block1相比，升级了传感器。
To investigate the rolling control characteristics of canard-controlled missile with fixed-tail, a numerical simulation method based on N-S formulation was conducted.
采用以N-S方程为主控方程的数值模拟方法，进行固定尾翼鸭式气动布局导弹的气动特性和流场数值模拟。
The sensor consists of a MEMS gyroscope, an accelerometer and microprocessor (MSC1214) and can output the rolling, pitch and yaw angular rate of rolling airframe missile.
利用一只重力加速度计和自行研制的MEMS陀螺作为敏感部件，利用MSC1214对两路信号处理，输出旋转弹的滚动、俯仰和偏航的角速率。
The sensor consists of a MEMS gyroscope, an accelerometer and microprocessor (MSC1214) and can output the rolling, pitch and yaw angular rate of rolling airframe missile.
利用一只重力加速度计和自行研制的MEMS陀螺作为敏感部件，利用MSC1214对两路信号处理，输出旋转弹的滚动、俯仰和偏航的角速率。
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