基于特征模型的火箭发动机伺服控制系统设计

摘要

以新型大推力火箭发动机为研究对象，提出了基于特征模型的伺服系统控制器设计方法。首先，介绍了特征建模理论并讨论了特征模型参数范围；其次，采用人工蜂群算法实时估计火箭发动机伺服系统特征模型参数，使其满足特征模型输出与实际系统输出特性等价条件；最后，使用黄金分割自适应控制律保证系统在参数估计过程中的闭环稳定性，同时引入前馈跟踪控制律，逻辑积分控制律和逻辑微分控制律使伺服控制系统快速、精确跟踪线位移指令并改善动态性能。仿真结果表明，设计的火箭发动机伺服控制系统指令跟踪精度高，动态特性良好，鲁棒性强。%Servo system controller based on characteristic model was proposed for the new high⁃thrust rocket engine.Firstly,the characteristic modeling method was introduced and the range of parameters was discussed. Secondly,artificial bee colony algorithm was employed to estimate the characteristic model parameters of servo system in real time under the condition of equivalent output of characteristic model and actual system.Finally,golden section adaptive control law was introduced to stabilize the close⁃loop system in the process of parameters estimation,feedforward tracking control law,logical integral and logical derivative control law were also used to improve the performance of servo system. Simulation results demonstrate that the servo system controller can guarantee the accurate tracking of command and robustness to model uncertainty.