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

Simple item page
dc.contributor.authorPang, Shuwei
dc.contributor.authorJafari, Soheil
dc.contributor.authorNikolaidis, Theoklis
dc.contributor.authorLI, Qiuhong
dc.date.accessioned2021-12-06T15:30:14Z
dc.date.available2021-12-06T15:30:14Z
dc.date.issued2021-05-04
dc.description.abstractControl technologies are innovated to satisfy increasingly complicated control demands of gas turbine engines. In terms of limit protection control, a novel model-based multivariable limit protection control method, which is achieved by adaptive command reconstruction and multiple-control 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 logic. Five different combination modes of control loops, which represent the online control loop of last time instant and that of current time instant, is analyzed. Different command reconstructions are designed for these modes, which is based on static gain conversion of amplitude beyond limits by using an onboard model. The 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 limits. The 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.en_UK
dc.identifier.citationPang S, Jafari S, Nikolaidis T, Li Q. (2021) A novel model-based multivariable framework for aircraft gas turbine engine limit protection control. Chinese Journal of Aeronautics, Issue 34, Volume 12, December 2021, pp. 57-72en_UK
dc.identifier.issn1000-9361
dc.identifier.urihttps://doi.org/10.1016/j.cja.2021.04.002
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/17311
dc.language.isoenen_UK
dc.publisherElsevieren_UK
dc.rightsAttribution-NonCommercial-NoDerivatives 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/4.0/*
dc.subjectGas turbine engineen_UK
dc.subjectMultivariable controlen_UK
dc.subjectOnboard predictionen_UK
dc.subjectAmplitude conversionen_UK
dc.subjectCommand reconstructionen_UK
dc.subjectLimit protection controlen_UK
dc.titleA novel model-based multivariable framework for aircraft gas turbine engine limit protection controlen_UK
dc.typeArticleen_UK

Files

Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
aircraft_gas_turbine_engine_limit-2021.pdf
Size:
2.07 MB
Format:
Adobe Portable Document Format
Description:
Download
License bundle
Now showing 1 - 1 of 1
No Thumbnail Available
Name:
license.txt
Size:
1.63 KB
Format:
Item-specific license agreed upon to submission
Description:
Download

Collections

Staff publications (SATM)