A method of determining lpv variable gain controller

Abstract

The invention discloses a method for determining an LPV variable gain controller, comprising steps of obtaining a standard form of a controller solving problem of a linear system of an LPV system having undetermined parameters through model conversion according to a system modeling error and a LPV parameter online measurement deviation, converting the controller-solving problem of the linear system to a convex optimization problem of an linear positive matrix unequal formula, solving the linear positive matrix unequal formula to obtain a corresponding positive fixed parameter dependable matrixes X and Y by solving the linear matrix unequal formula, successively calculating the parameters CK1, BK1,and AK1 in the controller, and determining the parameter in the controller K according to the parameter in the controller K1. The method for determining the LPV variable gain controller can design a controller having the sole self-adjustment rule, guarantees the stability of the close-loop system and has good dynamic performance and robustness.

Description

technical field [0001] The invention relates to aerospace technology, in particular to a method for determining a linear parameter varying (LPV, Linear Parameter Varying) variable gain controller. Background technique [0002] The dynamic performance of hypersonic vehicles is affected by changing parameters, and these changing parameters constitute their workspace (such as altitude, Mach number, temperature, etc.). Using the LPV variable gain theory to design the control scheme, the controller can work in the entire working space, and the controller changes according to the parameters of the system model, so that the aircraft can always have good dynamic performance in the large envelope range during the entire flight and robustness. [0003] However, the method commonly used in the design of aircraft controllers in the prior art is gain scheduling technology. Although this technology can ensure that the system meets the required performance near each operating point, the h...

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Problems solved by technology

[0003] However, the method commonly used in the design of aircraft controllers in the prior art is gain scheduling technology. Although this technology can ensure that the system meets the required performance near each operating point, the height, speed, and Parameters such as angle of attack and dynamic pressure will change drastically with the change of flight trajectory, the system state is far away from the linearized equilibrium point, the system parameters change quickly, and the external disturbance is strong. There are obvious defects in the controller of the method, and the number of linear controllers that need to be designed also increases, which depends on a large number of numerical calculations, and cannot theoretically guarantee the control performance and stability of the system in the entire parameter range.

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