Abstract
The aerodynamic characteristics of aero-engine, which have a wide range of flight envelopes, vary drastically, so its controller is required to be able to adapt to a large range of parameter variations and have good robustness. To solve the above problem, based on the regional pole assignment, a new aero-engine multi-variable robust gain scheduled LPV control algorithm was proposed. Firstly, the Jacobian linearization method was used to obtain polynomial LPV model of aero-engine, which can describe its dynamic performance under certain conditions. Further, aiming at the polynomial LPV model, a LPV output feedback controller with the closed-loop system pole placement in a given region, which satisfied robust H∞ performance requirement, is designed using the LMI method. Then the grid method is used to transform the Lyapunov functional which depend on the scheduling parameters into a single Lyapunov function, which can guarantee the system has good steady performance. Finally, simulation studies have carried out based on a certain turbofan engine. The simulation results show that the designed controller can realize the accurate tracking of control commands with response time less than 1.6 s, over shoot less than 1% and steady-state tracking error less than 0.1%. The control system can guarantee the global stability and has good robustness in the design envelope.
Highlights
The aerodynamic characteristics of aero⁃engine, which have a wide range of flight envelopes, vary drasti⁃ cally,so its controller is required to be able to adapt to a large range of parameter variations and have good robust⁃ ness
The Jacobian linearization method was used to obtain polynomial LPV model of aero⁃engine, which can describe its dynamic performance under certain conditions
Fur⁃ ther, aiming at the polynomial LPV model, a LPV output feedback controller with the closed⁃loop system pole placement in a given region, which satisfied robust H∞ performance requirement, is designed using the LMI method
Summary
化问题解决: min γ ìï éê( Acl( ρ) ) TXcl( ρ) + Xcl( ρ) Acl( ρ) + Ẋ cl( ρ) ïï ëê í Ï ïMD(r,q)( Acl( ρ) ,Xcl( ρ) ) < 0 (14) 式中矩阵变量 Xcl 和控制器参数矩阵 Aki , Bki ,Cki ,Dki 呈现非线性关系,为此,本文采用变量替 换法将上述非线性矩阵不等式转化为 LMI,以求解 ËêY( Ai + B2i Dki C2i ) X + NBki C2i X + YB2i Cki MT + NAki MT
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