An anti-wind-up controller design for rocket control systems with control input saturation

Jhoon Kim, H. D. Choi, J. H. Lee, D. S. Lee

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

An anti-wind-up controller for the attitude control of a two-stage sounding rocket has been designed. Once the actuator comes up to saturation limits, a feedback signal is generated in this controller from the difference between the compensator output and the actuator control input, and is used to make the actuator work in linear ranges. When this type of controller was applied to the two-stage sounding rocket attitude control system, a remarkable improvement was made in the control performance as compared with the PID (proportional, integral, plus derivative) controller case. Since the performance of this anti-wind-up controller was sensitive to the variation of control gains, a modified anti-wind-up controller has been also proposed to compensate for this.

Original languageEnglish
Pages (from-to)261-269
Number of pages9
JournalProceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Volume212
Issue number4
DOIs
Publication statusPublished - 1998 Jan 1

Fingerprint

Rockets
Control systems
Controllers
Sounding rockets
Actuators
Attitude control
Gain control
Derivatives
Feedback

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Mechanical Engineering

Cite this

@article{e02ce063dcaf4c8abb70e1c07f734260,
title = "An anti-wind-up controller design for rocket control systems with control input saturation",
abstract = "An anti-wind-up controller for the attitude control of a two-stage sounding rocket has been designed. Once the actuator comes up to saturation limits, a feedback signal is generated in this controller from the difference between the compensator output and the actuator control input, and is used to make the actuator work in linear ranges. When this type of controller was applied to the two-stage sounding rocket attitude control system, a remarkable improvement was made in the control performance as compared with the PID (proportional, integral, plus derivative) controller case. Since the performance of this anti-wind-up controller was sensitive to the variation of control gains, a modified anti-wind-up controller has been also proposed to compensate for this.",
author = "Jhoon Kim and Choi, {H. D.} and Lee, {J. H.} and Lee, {D. S.}",
year = "1998",
month = "1",
day = "1",
doi = "10.1243/0954410981532423",
language = "English",
volume = "212",
pages = "261--269",
journal = "Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering",
issn = "0954-4100",
publisher = "SAGE Publications Ltd",
number = "4",

}

An anti-wind-up controller design for rocket control systems with control input saturation. / Kim, Jhoon; Choi, H. D.; Lee, J. H.; Lee, D. S.

In: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Vol. 212, No. 4, 01.01.1998, p. 261-269.

Research output: Contribution to journalArticle

TY - JOUR

T1 - An anti-wind-up controller design for rocket control systems with control input saturation

AU - Kim, Jhoon

AU - Choi, H. D.

AU - Lee, J. H.

AU - Lee, D. S.

PY - 1998/1/1

Y1 - 1998/1/1

N2 - An anti-wind-up controller for the attitude control of a two-stage sounding rocket has been designed. Once the actuator comes up to saturation limits, a feedback signal is generated in this controller from the difference between the compensator output and the actuator control input, and is used to make the actuator work in linear ranges. When this type of controller was applied to the two-stage sounding rocket attitude control system, a remarkable improvement was made in the control performance as compared with the PID (proportional, integral, plus derivative) controller case. Since the performance of this anti-wind-up controller was sensitive to the variation of control gains, a modified anti-wind-up controller has been also proposed to compensate for this.

AB - An anti-wind-up controller for the attitude control of a two-stage sounding rocket has been designed. Once the actuator comes up to saturation limits, a feedback signal is generated in this controller from the difference between the compensator output and the actuator control input, and is used to make the actuator work in linear ranges. When this type of controller was applied to the two-stage sounding rocket attitude control system, a remarkable improvement was made in the control performance as compared with the PID (proportional, integral, plus derivative) controller case. Since the performance of this anti-wind-up controller was sensitive to the variation of control gains, a modified anti-wind-up controller has been also proposed to compensate for this.

UR - http://www.scopus.com/inward/record.url?scp=0032463871&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0032463871&partnerID=8YFLogxK

U2 - 10.1243/0954410981532423

DO - 10.1243/0954410981532423

M3 - Article

AN - SCOPUS:0032463871

VL - 212

SP - 261

EP - 269

JO - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

JF - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

SN - 0954-4100

IS - 4

ER -