Aeroelastic response of flapped-wing systems using robust estimation control methodology

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

doi:10.2514/1.15015

Aeroelastic response of flapped-wing systems using robust estimation control methodology

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

Research output: Contribution to journal › Review article › peer-review

11 Citations (Scopus)

Abstract

A study on the aeroelastic response and control of three-degree-of-freedom flapped-wing systems operating in an incompressible, subcritical flight speed and exposed to sonic boom loads, is presented. Kalman filter (KF) and sliding-mode observer (SMO) were both implemented to prevent system instability and reduction in performance due to spillover effects. The linear-quadratic- Gaussian (LQG) control strategy using SMO was used, and the feedback control was implemented via the estimated states. The feedback control system makes use of one measurement, which enables computation with less effort, and simulates the worse problem due to sensor failure.

Original language	English
Pages (from-to)	199-203
Number of pages	5
Journal	Journal of Guidance, Control, and Dynamics
Volume	29
Issue number	1
DOIs	https://doi.org/10.2514/1.15015
Publication status	Published - 2006

Bibliographical note

Funding Information:
Sungsoo Na acknowledges the support by the Basic Research Program of the Korea Science and Engineering Foundation, Grant R01-2002-000-00129-0.

ASJC Scopus subject areas

Control and Systems Engineering
Aerospace Engineering
Space and Planetary Science
Electrical and Electronic Engineering
Applied Mathematics

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Cite this

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abstract = "A study on the aeroelastic response and control of three-degree-of-freedom flapped-wing systems operating in an incompressible, subcritical flight speed and exposed to sonic boom loads, is presented. Kalman filter (KF) and sliding-mode observer (SMO) were both implemented to prevent system instability and reduction in performance due to spillover effects. The linear-quadratic- Gaussian (LQG) control strategy using SMO was used, and the feedback control was implemented via the estimated states. The feedback control system makes use of one measurement, which enables computation with less effort, and simulates the worse problem due to sensor failure.",

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

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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 by the Basic Research Program of the Korea Science and Engineering Foundation, Grant R01-2002-000-00129-0.

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N2 - A study on the aeroelastic response and control of three-degree-of-freedom flapped-wing systems operating in an incompressible, subcritical flight speed and exposed to sonic boom loads, is presented. Kalman filter (KF) and sliding-mode observer (SMO) were both implemented to prevent system instability and reduction in performance due to spillover effects. The linear-quadratic- Gaussian (LQG) control strategy using SMO was used, and the feedback control was implemented via the estimated states. The feedback control system makes use of one measurement, which enables computation with less effort, and simulates the worse problem due to sensor failure.

AB - A study on the aeroelastic response and control of three-degree-of-freedom flapped-wing systems operating in an incompressible, subcritical flight speed and exposed to sonic boom loads, is presented. Kalman filter (KF) and sliding-mode observer (SMO) were both implemented to prevent system instability and reduction in performance due to spillover effects. The linear-quadratic- Gaussian (LQG) control strategy using SMO was used, and the feedback control was implemented via the estimated states. The feedback control system makes use of one measurement, which enables computation with less effort, and simulates the worse problem due to sensor failure.

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Aeroelastic response of flapped-wing systems using robust estimation control methodology

Abstract

Bibliographical note

ASJC Scopus subject areas

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