基于虚拟飞行仿真的导弹控制系统设计

Design of Missile Control System Based on Virtual Flight Simulation

根据风洞虚拟飞行仿真系统的特点以及试验要求,设计了用于风洞虚拟飞行仿真的模型导弹的俯仰、偏航和滚转通道控制系统。导弹俯仰通道采用了迎角指令控制的三回路闭环控制结构,滚转通道采用了滚转姿态角指令控制的两回路闭环控制结构,而偏航通道采用液压驱动机构来开环控制侧滑角。利用极点配置法设计了俯仰和滚转通道的控制增益。最后通过数字仿真对所设计的控制系统进行了仿真验证。从数字仿真结果可以看出,无论是时域还是频域,所设计的俯仰和滚转通道闭环控制系统均能满足风洞虚拟飞行仿真的要求。

In this paper, according to the characteristics and demands of wind tunnel virtual flight simulation system, we de sign the control system of model missile pitch, yaw and roll channels for wind tunnel virtual flight simulations. In missile pitch channel, the three closeloop control structure is used for angle of attack command control. In missile roll channel, the two closeloop control structure is used for angle of roll attitude command control. In missile yaw channel, angle of sideslip is controlled by hydraulic driving device in open loop. The control system gains were designed through poleplacement method. Finally, the digital simulation is carried out and the design results are validated. Seeing from the digital simulation results, the designed pitch and roll channel closeloop control system can meet the demand of wind tunnel virtual flight simulation in time domain or frequency domain.