The composition of the simulation system, data processing flowchart and simulation mode that included the missile dynamics, sensitive element and variable structure controller were given.
给出了该仿真系统的组成、信号处理流程，以及包括弹体动力学、敏感元件和变结构控制器的仿真模型。
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。
For an A/A missile, its dynamics is separated into two parts, the dynamics of fast state and the dynamics of slow state based on the two timescale separation.
以某型空空导弹为对象，基于双时标的假设，将导弹动力学模态分离为快变状态动力学模态和慢变状态动力学模态，并对其分别进行了动态逆设计。
According to the demand of flight control system, a nonlinear dynamics model with considerable aerodynamic forces and moments for a large maneuver re entry missile head is built.
根据飞行控制要求，考虑了影响较大的气动力和气动力矩因素，建立了一个完全表征大机动情况下弹头运动的非线性动力学模型。
Making use of computational fluid dynamics method and dynamic simulation, the thesis studies the effects of jet flow on launch process of vehicular container-type missile.
结合流场计算和发射动力学仿真，研究某型车载发射系统中燃气流对发射过程的影响。
The filter dynamics are built in the three dimensional engagement scenario and the states are composed of relative position, velocity, missile acceleration and target acceleration.
在三维坐标下，创建包含导弹运动方程、目标运动方程、弹目相对运动方程的滤波模型。
The filter dynamics are built in the three dimensional engagement scenario and the states are composed of relative position, velocity, missile acceleration and target acceleration.
在三维坐标下，创建包含导弹运动方程、目标运动方程、弹目相对运动方程的滤波模型。
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