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A novel model-based multivariable framework for aircraft gas turbine engine limit protection control

A novel model-based multivariable framework for aircraft gas turbine engine limit protection control

作     者:Shuwei PANG Soheil JAFARI Theoklis NIKOLAIDIS Qiuhong LI Shuwei PANG;Soheil JAFARI;Theoklis NIKOLAIDIS;Qiuhong LI

作者机构:Jiangsu Province Key Laboratory of Aerospace Power SystemNanjing University of Aeronautics and AstronauticsNanjing 210016China Propulsion Engineering CenterSchool of AerospaceTransport and ManufacturingCranfield UniversityBedford MK43 OALUK 

出 版 物:《Chinese Journal of Aeronautics》 (中国航空学报(英文版))

年 卷 期:2021年第34卷第12期

页      面:57-72页

核心收录:

学科分类:082502[工学-航空宇航推进理论与工程] 08[工学] 0825[工学-航空宇航科学与技术] 

基  金:supported by China Scholarship Council(No.201906830081) 

主  题:Amplitude conversion Command reconstruction Gas turbine engine Limit protection control Multivariable control Onboard prediction 

摘      要:Control technologies are innovated to satisfy increasingly complicated control demands of gas turbine *** terms of limit protection control,a novel model-based multivariable limit protection control method,which is achieved by adaptive command reconstruction and multiplecontrol loop selection and switch logic,is proposed in this paper to address the problem of balancing smaller thrust loss and safe operations by comparing with widely-used Min-Max *** different combination modes of control loops,which represent the online control loop of last time instant and that of current time instant,is *** command reconstructions are designed for these modes,which is based on static gain conversion of amplitude beyond limits by using an onboard *** double-prediction based control loop selection and switch logic is developed to choose a control loop appropriately by comparing converted amplitude beyond limits regardless of one or more parameters tending to exceed *** proposed method is implemented in a twin-spool turbofan engine to achieve limit protection with direct thrust control,and the loss of thrust is improved by about 30% in comparison with the loss of thrust caused by Min-Max logic when limit protection control is activated,which demonstrates the effectiveness of the proposed method.

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