自旋激光驾束导弹转速及转角的计算与仿真

自旋激光驾束导弹实时仿真系统旨在研究该导弹的转速、转角的近似计算和解决姿态控制时执行机构－姿态控制发动机在点火时刻的空间位置问题。该系统仿真采用海鹰工作站解算导弹运动方程组。通过80C196KC的D／A实时输出导弹有关诸元。根据该导弹低转速和计算周期短的特点，以两相邻基准脉冲信号作为控制周期，将转速转化为相应控制周期内的角度增量，简化了滚转角速度在控制器中的计算，实时仿真表明，此近似计算结果满足制导要求。

The Calculation and Simulation of Rotational Speed and Angle for Spinning Missile

Approximate calculations on rotational speed and angle of spinning missile under laser beam ride guidance for real time simulation are investigated, and a problem of obtaining the space position of an actuator that is an attitude control motor and carrying out attitude control is resolved. The equations of motions of missile are calculated with sea glede workstation in the simulation system, and the set of data relation to missile is exported in reel time through D/A of 80C196KC. According as characteristics of low rotating velocity of the missile as well as short calculating period, two datum pulses of an interval bitewing was defined as a steering period, the rotational speed was converted to the angle increment in each control period to simple the calculation in controller. The real time simulations indicate that the results of approximate calculation meet the requirement of the guidance system.