Robust aeroelastic control of flapped wing systems using a sliding mode observer

Sungsoo Na; Liviu Librescu; Myung Hyun Kim; In Joo Jeong; Pier Marzocca

doi:10.1016/j.ast.2005.10.002

Robust aeroelastic control of flapped wing systems using a sliding mode observer

Sungsoo Na, Liviu Librescu, Myung Hyun Kim, In Joo Jeong, Pier Marzocca

Research output: Contribution to journal › Article › peer-review

35 Citations (Scopus)

Abstract

The performance of a robust control strategy applied to a three-degrees-of-freedom (3-DOF) flap-wing aeroelastic system impacted by a pressure pulse in the subcritical flight speed regime is investigated. The goal of its implementation is to suppress flutter instability and reduce the vibrational level in the subcritical flight speed range. To this end, the linear quadratic Gaussian (LQG) control methodology in conjunction with a sliding mode observer (SMO) are used. Comparisons with the counterpart results obtained via implementation of LQG controller with conventional Kalman filter (KF) are also provided and pertinent conclusions are outlined.

Original language	English
Pages (from-to)	120-126
Number of pages	7
Journal	Aerospace Science and Technology
Volume	10
Issue number	2
DOIs	https://doi.org/10.1016/j.ast.2005.10.002
Publication status	Published - 2006 Mar

Keywords

Blast load
Flapped wing
Kalman filter
Robust aeroelastic control
Sliding mode observer

ASJC Scopus subject areas

Aerospace Engineering

Access to Document

10.1016/j.ast.2005.10.002

Cite this

@article{4edd3877acb944dc8e7bfa805fd4a13b,

title = "Robust aeroelastic control of flapped wing systems using a sliding mode observer",

abstract = "The performance of a robust control strategy applied to a three-degrees-of-freedom (3-DOF) flap-wing aeroelastic system impacted by a pressure pulse in the subcritical flight speed regime is investigated. The goal of its implementation is to suppress flutter instability and reduce the vibrational level in the subcritical flight speed range. To this end, the linear quadratic Gaussian (LQG) control methodology in conjunction with a sliding mode observer (SMO) are used. Comparisons with the counterpart results obtained via implementation of LQG controller with conventional Kalman filter (KF) are also provided and pertinent conclusions are outlined.",

keywords = "Blast load, Flapped wing, Kalman filter, Robust aeroelastic control, Sliding mode observer",

author = "Sungsoo Na and Liviu Librescu and Kim, {Myung Hyun} and Jeong, {In Joo} and Pier Marzocca",

note = "Funding Information: Sungsoo Na acknowledges the support of this work by the Basic Research Program of the Korea Science and Engineering Foundation, Grant No. R01-2002-000-00129-0.",

year = "2006",

month = mar,

doi = "10.1016/j.ast.2005.10.002",

language = "English",

volume = "10",

pages = "120--126",

journal = "Aerospace Science and Technology",

issn = "1270-9638",

publisher = "Elsevier Masson SAS",

number = "2",

}

TY - JOUR

T1 - Robust aeroelastic control of flapped wing systems using a sliding mode observer

AU - Na, Sungsoo

AU - Librescu, Liviu

AU - Kim, Myung Hyun

AU - Jeong, In Joo

AU - Marzocca, Pier

N1 - Funding Information: Sungsoo Na acknowledges the support of this work by the Basic Research Program of the Korea Science and Engineering Foundation, Grant No. R01-2002-000-00129-0.

PY - 2006/3

Y1 - 2006/3

N2 - The performance of a robust control strategy applied to a three-degrees-of-freedom (3-DOF) flap-wing aeroelastic system impacted by a pressure pulse in the subcritical flight speed regime is investigated. The goal of its implementation is to suppress flutter instability and reduce the vibrational level in the subcritical flight speed range. To this end, the linear quadratic Gaussian (LQG) control methodology in conjunction with a sliding mode observer (SMO) are used. Comparisons with the counterpart results obtained via implementation of LQG controller with conventional Kalman filter (KF) are also provided and pertinent conclusions are outlined.

AB - The performance of a robust control strategy applied to a three-degrees-of-freedom (3-DOF) flap-wing aeroelastic system impacted by a pressure pulse in the subcritical flight speed regime is investigated. The goal of its implementation is to suppress flutter instability and reduce the vibrational level in the subcritical flight speed range. To this end, the linear quadratic Gaussian (LQG) control methodology in conjunction with a sliding mode observer (SMO) are used. Comparisons with the counterpart results obtained via implementation of LQG controller with conventional Kalman filter (KF) are also provided and pertinent conclusions are outlined.

KW - Blast load

KW - Flapped wing

KW - Kalman filter

KW - Robust aeroelastic control

KW - Sliding mode observer

UR - http://www.scopus.com/inward/record.url?scp=33644773508&partnerID=8YFLogxK

U2 - 10.1016/j.ast.2005.10.002

DO - 10.1016/j.ast.2005.10.002

M3 - Article

AN - SCOPUS:33644773508

SN - 1270-9638

VL - 10

SP - 120

EP - 126

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

IS - 2

ER -

Robust aeroelastic control of flapped wing systems using a sliding mode observer

Abstract

Keywords

ASJC Scopus subject areas

Access to Document

Other files and links

Fingerprint

Cite this