公开(公告)号：US11454177B2

公开(公告)日：2022-09-27

申请号：US16462519

申请日：2018-06-15

Applicant: Dalian University of Technology

Inventor： Xian Du ,  Yanhua Ma ,  Ximing Sun ,  Zhimin Wang

IPC: F02C9/00 ,  F02C9/28 ,  G05B17/02 ,  G06F17/16 ,  B64D31/06 ,  G06F30/15 ,  G06F111/10

Abstract: A design method of aero-engine on-line optimization and multivariable control based on model prediction control realizes aero-engine multivariable control and on-line optimization according to thrust, rotational speed and other needs under the condition of meeting constraints. The first part is a prediction model acquisition layer that continuously establishes a small deviation linear model of an aero-engine near different steady state points based on the actual operating state of the aero-engine in each control cycle and external environment parameters and that supplies model parameters to a controller; and the second part is a control law decision-making layer which is a closed loop structure that consists of a model prediction controller and an external output feedback. The model prediction controller determines the output of the controller at next moment by solving a linear optimization problem according to an engine model in the current state, a control instruction and relevant constraints.