摘要
某鸭式布局的制导炮弹,采用自旋尾翼的方式可实现鸭舵对弹体的滚转控制。基于小扰动假设推导出制导弹滚转运动的扰动方程,分析了滚转运动特性及鸭舵偏转对滚转运动的影响,建立了相应的滚转运动稳定回路模型,回路中滚转控制用比例微分(PD)控制方式来实现。采用Matlab/Simlink软件建立了制导弹滚转控制的仿真模型,根据系统的性能要求用Simulink中的Simulink Response Optimization模块对控制系统进行了优化设计。结果显示弹体滚转位置0.2s可以控制到位,设计结果较好地满足了滚转控制系统品质指标的要求。
The canard configuration guided projectilemade use of free-spinning tail.This kind of mode can realize rolling control of the canard to projectile body.Based on the small disturbance hypothesis,rolling motion disturbance equations were deduced.The rolling motion features and the influence of canard deflection onrolling motion were analyzed.Related stable loop model of rolling motion was set up by means of PD control mode.Using Maltlab/Simulink software,a simulation model of guided projectile rolling controller was designed.According to the response optimization module in Simulink software,optimization design of the rollingcontrol system was carried out.The simulation results showed that the rolling control of guided projectile needs 0.2 second.The design results can also preferably meet the requirements of rolling control system index.
出处
《火炮发射与控制学报》
北大核心
2011年第3期56-59,共4页
Journal of Gun Launch & Control
关键词
飞行器控制、导航技术
制导炮弹
简易制导
滚转控制
优化设计
control and navigation technology of aerocraft
guided projectile
simplified guidance
rolling control
optimum design
