论文部分内容阅读
在飞行控制系统优化设计中,由于系统存在多输入、多输出的模型结构,古典控制方法无法应用到MIMO系统中,尤其现代控制方法设计过程中一次性计算出反馈控制器,导致应用过程中可靠性降低,对古典飞行控制系统控制结构进行优化设计。控制系统内回路采用EA方法,外回路适当引入误差积分控制和前馈比例控制,进而针对广义被控对象直接进行控制律设计与仿真。运用根轨迹方法对控制系统进行验证分析,并根据实际需求对控制律进行适当改进。仿真结果表明,特征结构配置方法能够较好的与古典控制理论相结合,完成指令跟踪控制律设计,且具有很好的鲁棒性和动态特性,新的控制结构应用起来方便有效。
In the optimization design of flight control system, the classical control method can not be applied to the MIMO system due to the multi-input and multi-output model structure in the system. Especially, the feedback controller is calculated once during the design of modern control methods, which leads to reliable application Reduce sex, optimize the control structure of classical flight control system. EA method is used in the control loop of the control system, error integral control and feedforward proportional control are introduced properly in the outer loop, and then the control law design and simulation are directly carried out for the generalized controlled object. The root locus method is used to verify and analyze the control system, and the control law is appropriately improved according to the actual demand. The simulation results show that the method of feature structure configuration can be well combined with the classical control theory to complete the design of command tracking control law, and has good robustness and dynamic characteristics. The new control structure is convenient and effective.