基于Matlab/Simulink的旋转导弹六自由度弹道仿真

Six-degrees-of-freedom Trajectory Simulation of Rotating Missile Based on Matlab/Simulink

旋转导弹弹道仿真是弹翼结构优化设计和弹道优化设计的基础。首先用CFD方法计算了旋转导弹在不同转速、攻角、侧滑角和马赫数下的气动系数,其次介绍了Matlab/Simulink的航空模块集,并利用其建立了旋转导弹的六自由度弹道仿真的方框图模型,仿真过程中的气动系数利用已计算得到的系数表经四维插值获得,最后给出了静止大气和风场中的弹道仿真结果。从仿真的结果可以看出,旋转导弹的攻角和侧滑角随弹体的轴向旋转而作振荡变化,并且轴向高速旋转有助于保持法向和横向的稳定性。

Trajectory simulation of rotating missile is the basis of optimization designs for fins of missile and trajectory. Aerodynamic coefficients of rotating missile in different of rotating velocity, attach angle, yaw angel and mach number are computed firstly, aerospace block-set of Matlab/Simulink is presented and the model of block diagram of six-degrees-of-freedom （6-DOF） trajectory simulation of rotating missile is constructed, aerodynamic coefficients used in simulation are computed by 4-dimension interpolation method. The results of trajectory simulation in static atmosphere and wind field are computed and analyzed finally. Form the results of simulation, we can find that attack angel and yaw angel surge with axial rotation, and the high axial rotating rate is helpful for stability of normal and lateral directions.