Turbojet thrust augmentation through a variable exhaust nozzle with active disturbance rejection control

Francisco Villarreal-Valderrama, Patricia Zambrano-Robledo, Diana Hernandez-Alcantara, Luis Amezquita-Brooks

1 Citation (Scopus)

Abstract

Turbojets require variable exhaust nozzles to fit high-demanding applications; however, few reports on nozzle control are available. The purpose of this paper is to investigate the possible advantages of an exhaust gas control through a variable exhaust nozzle. The control design method combines successful linear active disturbance rejection control (LADRC) capabilities with a loop shaping controller (LSC) to: (i) allow designing the closed-loop characteristics in terms of gain margin, phase margin and bandwidth, and (ii) increase the LSC disturbance rejection capabilities with an extended state observer. A representation of the nozzle dynamics is obtained from first principles and adapted to achieve a stream-velocity-based control loop. The results show that the resulting controller allows improving the expansion of the exhaust gas to the ambient pressure for the whole operating range of the turbojet, increasing the estimated thrust by 14.23% during the tests with experimental data.

Original languageEnglish
Article number293
JournalAerospace
Volume8
Issue number10
DOIs
Publication statusPublished - Oct 2021

Bibliographical note

Funding Information:
Funding: This research was funded by CONACYT under the program Fondo Institucional de Fomento Regional para el Desarrollo Científico, Tecnológico y de Innovación FORDECYT. The APC was funded by Universidad de Monterrey and Universidad Autónoma de Nuevo León.

Funding Information:
Acknowledgments: The authors would like to thank the support provided by the “Fondo Insti-tucional de Fomento Regional para el Desarrollo Científico, Tecnológico y de Innovación” from CONACYT (FORDECYT).

Funding Information:
This research was funded by CONACYT under the program Fondo Institucional de Fomento Regional para el Desarrollo Cient?fico, Tecnol?gico y de Innovaci?n FORDECYT. The APC was funded by Universidad de Monterrey and Universidad Aut?noma de Nuevo Le?n.Acknowledgments: The authors would like to thank the support provided by the ?Fondo Insti-tucional de Fomento Regional para el Desarrollo Cient?fico, Tecnol?gico y de Innovaci?n? from CONACYT (FORDECYT).

Publisher Copyright:
© 2021 by the authors. Licensee MDPI, Basel, Switzerland.

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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