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Wang, Z.,Behal, A.,Marzocca, P. The Korean Society for Aeronautical and Space Scie 2010 International Journal of Aeronautical and Space Sc Vol.11 No.4
Active aeroelastic control is an emerging technology aimed at providing solutions to structural systems that under the action of aerodynamic loads are prone to instability and catastrophic failures, and to oscillations that can yield structural failure by fatigue. The purpose of the aeroelastic control among others is to alleviate and even suppress the vibrations appearing in the flight vehicle subcritical flight regimes, to expand its flight envelope by increasing the flutter speed, and to enhance the post-flutter behavior usually characterized by the presence of limit cycle oscillations. Recently adaptive and robust control strategies have demonstrated their superiority to classical feedback strategies. This review paper discusses the latest development on the topic by the authors. First, the available control techniques with focus on adaptive control schemes are reviewed, then the attention is focused on the advanced single-input and multi-input multi-output adaptive feedback control strategies developed for lifting surfaces operating at subsonic and supersonic flight speeds. A number of concepts involving various adaptive control methodologies, as well as results obtained with such controls are presented. Emphasis is placed on theoretical and numerical results obtained with the various control strategies.
Robust Adaptive Output Feedback Control Design for a Multi-Input Multi-Output Aeroelastic System
Wang, Z.,Behal, A.,Marzocca, P. The Korean Society for Aeronautical and Space Scie 2011 International Journal of Aeronautical and Space Sc Vol.12 No.2
In this paper, robust adaptive control design problem is addressed for a class of parametrically uncertain aeroelastic systems. A full-state robust adaptive controller was designed to suppress aeroelastic vibrations of a nonlinear wing section. The design used leading and trailing edge control actuations. The full state feedback (FSFB) control yielded a global uniformly ultimately bounded result for two-axis vibration suppression. The pitching and plunging displacements were measurable; however, the pitching and plunging rates were not measurable. Thus, a high gain observer was used to modify the FSFB control design to become an output feedback (OFB) design while the stability analysis for the OFB control law was presented. Simulation results demonstrate the efficacy of the multi-input multi-output control toward suppressing aeroelastic vibrations and limit cycle oscillations occurring in pre- and post-flutter velocity regimes.
Theoretical Aspects Of Innovation Processes In The Holistic Educational Process
Prokopenko, Alona,Chukhrai, Liubov,Behal, Tetiana,Pustovalov, Sergii,Kliuchko, Yuliia,Khimchuk, Liliana International Journal of Computer ScienceNetwork S 2022 International journal of computer science and netw Vol.22 No.6
The article is devoted to the research and search for effective pedagogical technologies. The definitions of "innovation", "technologicalization", "pedagogical technology" are analyzed. "Innovative pedagogical technology". The blocks that make up the innovative processes in education are studied. The importance and role of innovations in education (vocational education) are clarified. The components of pedagogical technology are studied: conceptual, content-procedural and professional. The signs of classifications of pedagogical technologies are investigated. The stages of evolution of the definition of "pedagogical technology", as well as the levels of its application in pedagogical science are highlighted. Criteria of manufacturability and signs of pedagogical technology are investigated.The algorithm for the analysis of pedagogical technology is investigated: identification of technology; name of technology; conceptual principles; the content of education; activity characteristics; organizational and methodological support of the educational process. Pedagogical technologies that should be implemented in vocational education institutions are analyzed.
Robust Adaptive Output Feedback Control Design for a Multi-Input Multi-Output Aeroelastic System
Z. Wang,A. Behal,P. Marzocca 한국항공우주학회 2011 International Journal of Aeronautical and Space Sc Vol.12 No.2
In this paper, robust adaptive control design problem is addressed for a class of parametrically uncertain aeroelastic systems. A full-state robust adaptive controller was designed to suppress aeroelastic vibrations of a nonlinear wing section. The design used leading and trailing edge control actuations. The full state feedback (FSFB) control yielded a global uniformly ultimately bounded result for two-axis vibration suppression. The pitching and plunging displacements were measurable; however, the pitching and plunging rates were not measurable. Thus, a high gain observer was used to modify the FSFB control design to become an output feedback (OFB) design while the stability analysis for the OFB control law was presented. Simulation results demonstrate the efficacy of the multi-input multi-output control toward suppressing aeroelastic vibrations and limit cycle oscillations occurring in pre- and post-flutter velocity regimes.
Z. Wang,A. Behal,P. Marzocca 한국항공우주학회 2010 International Journal of Aeronautical and Space Sc Vol.11 No.4
Active aeroelastic control is an emerging technology aimed at providing solutions to structural systems that under the action of aerodynamic loads are prone to instability and catastrophic failures, and to oscillations that can yield structural failure by fatigue. The purpose of the aeroelastic control among others is to alleviate and even suppress the vibrations appearing in the flight vehicle subcritical flight regimes, to expand its flight envelope by increasing the flutter speed, and to enhance the postflutter behavior usually characterized by the presence of limit cycle oscillations. Recently adaptive and robust control strategies have demonstrated their superiority to classical feedback strategies. This review paper discusses the latest development on the topic by the authors. First, the available control techniques with focus on adaptive control schemes are reviewed, then the attention is focused on the advanced single-input and multi-input multi-output adaptive feedback control strategies developed for lifting surfaces operating at subsonic and supersonic flight speeds. A number of concepts involving various adaptive control methodologies, as well as results obtained with such controls are presented. Emphasis is placed on theoretical and numerical results obtained with the various control strategies.
Zhang, K.,Wang, Z.,Behal, A.,Marzocca, P. The Korean Society for Aeronautical and Space Scie 2012 International Journal of Aeronautical and Space Sc Vol.13 No.2
The model-free control of aeroelastic vibrations of a non-linear 2-D wing-flap system operating in supersonic flight speed regimes is discussed in this paper. A novel continuous robust controller design yields asymptotically stable vibration suppression in both the pitching and plunging degrees of freedom using the flap deflection as a control input. The controller also ensures that all system states remain bounded at all times during closed-loop operation. A Lyapunov method is used to obtain the global asymptotic stability result. The unsteady aerodynamic load is considered by resourcing to the non-linear Piston Theory Aerodynamics (PTA) modified to account for the effect of the flap deflection. Simulation results demonstrate the performance of the robust control strategy in suppressing dynamic aeroelastic instabilities, such as non-linear flutter and limit cycle oscillations.
K. Zhang,Z. Wang,A. Behal,P. Marzocca 한국항공우주학회 2012 International Journal of Aeronautical and Space Sc Vol.13 No.2
The model-free control of aeroelastic vibrations of a non-linear 2-D wing-flap system operating in supersonic flight speed regimes is discussed in this paper. A novel continuous robust controller design yields asymptotically stable vibration suppression in both the pitching and plunging degrees of freedom using the flap deflection as a control input. The controller also ensures that all system states remain bounded at all times during closed-loop operation. A Lyapunov method is used to obtain the global asymptotic stability result. The unsteady aerodynamic load is considered by resourcing to the non-linear Piston Theory Aerodynamics (PTA) modified to account for the effect of the flap deflection. Simulation results demonstrate the performance of the robust control strategy in suppressing dynamic aeroelastic instabilities, such as non-linear flutter and limit cycle oscillations.
Modern Pedagogical Technologies: Optimization And Provision Of Educational Activities
Pustovalov, Serhii,Kliuchko, Yuliia,Chukhrai, Liubov,Behal, Tetiana,Cherniakova, Zhanna,Genkal, Svitlana International Journal of Computer ScienceNetwork S 2021 International journal of computer science and netw Vol.21 No.12
The article substantiates the need to use innovative pedagogical technologies as an effective mechanism for implementing the idea of advanced vocational education, highlights the main components of the idea of anticipation, highlights the experience of using modern technologies in institutions of secondary vocational education. The purpose of the study is to increase the level of professional training of qualified workers and specialists through the effective choice of methodological tools aimed at the formation of professional competencies on the basis of an educational institution.