摘要
为改善传统基于线性控制方法(PID控制)设计航空发动机控制系统在极限保护方面的不足,提出利用非线性控制理论——滑模控制取代原有控制系统中的线性控制器,设计了发动机稳态控制器与基于max-min控制逻辑的极限保护器的综合系统。与传统PID控制方法的控制效果相比较,滑模控制方法可在保证发动机不超限的情况下充分发挥发动机潜能。讨论了边界层厚度等因素对滑模控制抖动的影响。采用滑模方法设计的控制器在硬件在回路平台(HIL)上通过了仿真验证,满足实时性要求。
In order to improve inherent vice in limit protection which were designed by traditional method of aeroengine control system based on linear regulators （PID）, a nonlinear control method on Sliding Mode Control （SMC）replaced the usual PID regulators was proposed. The steady-state controller was combined with limit regulators based on the traditional max-rain selector system. Compared with controller by PID, the controller by SMC can ensure that engine have a better performance with the prescribed limits. Effects of parameters such as the boundary layer thickness on sliding mode were discussed. SMC system was applied on a hardware-in-the-loop real-time simulation platform. Results show that the method can meet the real-time requirements.
出处
《航空发动机》
2015年第6期33-38,共6页
Aeroengine
