Method for determining stability of LPV controller

Abstract

he 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 and converting the controller-solving problem of the linear system to a convex optimization problem of an linear positive matrix unequal formula, wherein when the linear positive matrix can be solved , the LPV controller exists and is stable, The method for determining stability of LPV controller can determine the stability of the LPV controller and obtains the sufficient conditions for the controller to exist.

Description

technical field [0001] The invention relates to aerospace technology, in particular to a method for determining the stability of a Linear Parameter Varying (LPV, Linear Parameter Varying) controller. Background technique [0002] The dynamic characteristics of hypersonic vehicles are highly nonlinear, and the system parameters change drastically in a wide range, so the general linear control system obviously cannot meet the performance requirements of the system; in addition, due to the inevitable shortcomings such as the complexity of calculation, The existing nonlinear control system design methods are not suitable for engineering implementation. Therefore, the most commonly used engineering design method for systems such as hypersonic vehicles is variable gain control. The emergence of LPV theory makes up for the deficiency of traditional variable gain control, and the stability of LPV system can be proved theoretically. [0003] In the prior art, the traditional three-l...

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Problems solved by technology

Although the above-mentioned existing technologies can guarantee that the system meets the required performance at each operating point, they cannot theoretically guarantee the control performance and stability of the system in the entire parameter range

During the flight of a hypersonic vehicle, its altitude, speed, angle of attack, dynamic pressure and other parameters will change drastically with the change of the flight trajectory. The system state is far from the linear equilibrium point, and the system parameters change rapidly. , the external disturbance is strong, so the controller of the traditional gain preset method has obvious defects

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