摘要
针对某型航空用二冲程发动机,用逐步回归的方法建立发动机非线性稳态模型,在平衡点附近进行泰勒级数展开,得到了发动机在平衡点附近的线性模型;基于线性矩阵不等式(LMI)的方法进行鲁棒控制算法研究,得到了鲁棒PI控制参数,实现了系统的鲁棒控制;基于模糊T-S模型并行分配补偿控制策略,设计了控制算法切换策略.经系统仿真和发动机台架实验验证,在负载11%的扰动下转速控制精度稳定在2.3%之内,控制器对于外界干扰有较强的鲁棒性,得到了期望的控制效果.
A nonlinear two-stroke engine model was constructed using a mathematical tool of stepwise regression. Taylor expansion method was used around an equilibrium point during the linearizing process, and the linearized model was reached. A method for designing robust proportional integral (PI) controller was presented. The problem of parameter desig ning of the robust PI controller was solved with linear matrix inequalities (LMIs) approach. The controller switching was designed based on the idea of parallel distributed compensation (PDC) to Takagi Sugeno fuzzy model. Simulation and experiments on the engine dynamome ter show that the proposed controller can keep the engine speed in 2.3% under 11% disturb ance and can achieve the anticipated robust performance.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第11期2128-2132,共5页
Journal of Aerospace Power