• 안보군사학연구
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• 통권1호
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• pp.311-343
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• 2003

In this paper, we propose a generalized disturbance torque suppression control scheme of servo motors for missile fin actuators. Our controller consists of both a model based feed-forward controller and a stabilizing feedback controller. The feed-forward controller is designed such that the output of nominal plant tracks perfectly the reference position command with a desired dynamic characteristics. The feedback controller stabilizes the overall closed loop system. Furthermore, the feedback controller contains a free function that can be chosen arbitrary. The free function can be designed so as to achieve both the suppression of disturbances and the robustness to model uncertainties. In order to illuminate the superior performance of our control scheme to the conventional ones, we present some simulation results.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2007년도 추계학술대회논문집
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• pp.722-726
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• 2007

In this paper we deal with a design of the integral sliding mode controller to suppress the disturbance force acting on the suspension system of the magnetically levitated train system. One of the important factors that cause the disturbance force acting on the suspension system comes from the low propulsion speed of linear induction motor. In this paper integral sliding mode controller is employed to reject the disturbance force produced by the propulsion system of the linear induction motor. In order to show the effectiveness of the designed controller a dynamic simulation is utilized and the sliding mode controller without integral compensator is compared with the proposed integral sliding mode controller to suppress the disturbance force.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.162-167
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• 1994

An effective and disturbance suppressible controller can be obtained by assigning the left eigenstructure (eigenvalues/left eigenvectors) of a system. However, the disturbance decouplability is governed by the right eigenstructure(eigenvalues/right eigenvectors) of the system. In this paper, in order to obtain a disturbance decouplable as well as effective and disturbance suppressible controller, the concurrent assignment scheme of the left and right eigenstructure is proposed. The biorthogonality property between the left and right modal matrices of a system well as the relations between the achievable right modal matrix and states selection matrices are used to develop the scheme. The proposed concurrent eigenstructure assignment scheme guarantees that the desired eigenvalues are achieved exactly and the desired left and right eigenvectors are assigned to the best possible(achievable) sets of eigenvectors in the least square sense, respectively. A numerical example is presented to illustrate the usefulness of the proposed scheme.

• 방송공학회논문지
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• 제8권1호
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• pp.11-18
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• 2003

본 논문에서는 잡음 에너지에 의한 지각적 간섭현상 해석을 통한 지각적 컨벌루션 잡음 제어에 의한 음질 개선 방법을 연구하였다. 지각적 컨벌루션 잡음은 잡음에 의한 신호의 지각적인 특성 변화 및 잡음 추정오차에 의한 잔여 잡음의 영향을 반영하는 것이다. 실험 결과 임계대역 여기 에너지를 통한 지각적 부가 잡음 제어 필터와 순음도 변화도를 통한 지각적 컨벌루션 잡음 제어 필터가 대등한 음질 개선 성능을 나타내었으며, 다양한 잡음 환경에서도 우수한 음질 개선을 나타냄을 확인 할 수 있었다.

• 소음진동
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• 제6권5호
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• pp.567-574
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• 1996

This paper concerns an articulated space robot with flexible links. The equations of its motion are derived by means of the Lagrangian mechanics. Assuming that magnitude of elastic motions are relatively small, the perturbation approach is taken to separate the original equations of motion into linear and nonlinear equations. Th effect the desired payload motion, open loop control inputs are first determined based on the nonlinear equations. One the other hand, in order to reduce the positional errors during the maneuver, vibration suppression is actively done with a feedforward control for disturbance cancellation to some extent. Additionally, for performance robustness against residual disturbance, an LQ control modified to have a prescribed degree of stability is applied based on the linear equations. Measurement equations are formulated to be used for the maximum likelihood estimator to reconstruct states from the original robot equations of motion. Finally, numerical simulations show effectiveness of the proposed control design scheme.

• International Journal of Aeronautical and Space Sciences
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• 제7권2호
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• pp.121-127
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• 2006

An analysis procedure for the combined problem of control algorithm and aeroelastic system which is based on the computational fluid dynamics(CFD) technique has been developed. The aerodynamic forces in the transonic region are calculated from the transonic small disturbance(TSD) theory. An linear quadratic regulator(LQR) controller is designed to suppress the transonic flutter. The optimal control gain is estimated by solving the discrete-time Riccati equation. The system identification technique rebuilds the CFD-based aeroelstic system in order to form an adequate system matrix which involved in the discrete-time Riccati equation. Finally the controller, that is constructed on the basis of system identification technique, is used to suppress the flutter phenomenon of the airfoil with attached store. This approach, that is, the CFD-based aeroservoelasticity design, can be utilized for the development of effective flutter controller design in the transonic region.

• 한국전자통신학회논문지
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• 제7권4호
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• pp.839-848
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• 2012

본 논문에서는 외란토크를 효과적으로 억제할 수 있는 AC 서보모터의 견실제어 방법을 제안한다. 제안된 제어기는 플랜트 모델에 기초한 피드포워드제어기와 안정화 피드백제어기로 구성된다. 피드포워드제어기는 공칭(nominal) 플랜트의 출력이 기준 속도명령을 정확히 추적하도록 설계되며 피드백제어기는 전체 폐루프시스템을 안정화시키는 역할을 한다. 피드백제어기는 임의로 선택될 수 있는 자유함수를 포함하는데 이 자유함수는 외란토크의 영향을 억제하고 제어기가 모델오차에 견실하게(robust) 동작되도록 선택될 수 있다. 컴퓨터 시뮬레이션을 통하여 제안된 제어방식이 기존의 제어방식들에 비해 우수한 제어성능을 가짐을 입증한다.

• 대한전자공학회논문지TE
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• 제39권2호
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• pp.118-123
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• 2002

토크 전달시스템은 다수의 기어와 커플링이 유연하게 구성되어 있으므로, 모터의 속도가 갑자기 변할 때 비틀림 진동이 발생한다. 따라서 모터의 정확한 응답 특성을 얻기 위해서는 반드시 이 진동을 억제시켜야 한다. 이와 같이 진동억제는 모터제어에 있어서 매우 중요하다. 진동억제를 위해, 특히 2관성 시스템의 제어를 위해 다양한 제어방법들이 소개되었다. 토크의 비틀림 현상으로 인해 발생하는 진동을 억제하기 위해 토크의 비틀림 성분을 궤환시켜 외란 관측기 및 필터를 사용하여 진동을 억제하는 방법이 소개되었고, 이 방법은 CDM으로 적절한 비례 제어기와 필터의 계수 값을 설계하여 진동을 억제하는 방법이다. 그러나 CDM을 이용하여 설계된 제어기는 외란이 인가될 경우에 적응성이 떨어짐을 알 수 있다. 따라서 본 논문에서는 이러한 문제를 해결하기 위하여 퍼지를 사용하여 제어기의 파라메터 $K_P$를 자동적으로 추종하는 자동추정 퍼지제어기를 제안하고 이 제어기의 성능을 시뮬레이션을 통해 검증하였다.

• 제어로봇시스템학회논문지
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• 제1권1호
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• pp.4-12
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• 1995

In the sense of eigenstructure (eigenvalues/eignenvectors) assignment, the effectiveness and disturbance suppressibility of a controller depend mainly on the left eigenstructure (eignevalues/left eigenvectors) of a system. On the other hand, the disturbance decouplability is governed by the right eigenstructure (eignevalues/right eigenvectors) of the system. In this paper, in order to obtain a disturbance decouplable as well as effetive and disturbance suppressible controller, a concurrent assignment methodology of the left and right eigenstructure is proposed. The biorthogonality condition between the left and right modal matrix and state selection matrices are used to develop the methodology. The proposed concurrent eigenstructure assignment methodology guarantees that the desired eigenvalues are achieved exactly and the desired left and right eigenvectors are assigned to the best possible (achievable) sets of eigenvectors in the least square sense, respectively. A numerical example is presented to illustrate the validity and usefulness of the proposed methodology.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 1996년도 추계학술대회 논문집
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• pp.230-235
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• 1996

Eigenstructure (eigenvalues/eigenvectors) assignment has been shown to be a useful tool for flight control system design. In the sense of the eigenstructure assignment, the effectiveness and disturbance suppressibility of a controller depend mainly on the left eigenstructure (eigenvalues/left eigenvectors) of a system. On the other hand, the disturbance decouplability is governed by the right eigenstructure (eigenvalues/right eigenvectors) of the system. In this paper, in order to obtain a disturbance decouplable as well as effective and disturbance suppressible controller, a concurrent assignment methodology of the left and right eigenstructures is proposed. The biorthogonality condition between the left and right modal matrices of a system as well as the relations between the achievable right modal matrix and state selection matrices are used to develop the methodology. The proposed concurrent eigenstructure assignment methodology guarantees that the desired eigenvalues are achieved exactly and the desired left and right eigenvectors are assigned to the best possible(achievable) sets of eigenvectors in the least square sense, respectively. The proposed design methodology is applied to designing a lateral flight control system for an L-1011 aircraft with disturbances.